FIREBOLT
FILE INFORMATION
FILENAME(S): FIREBOLT
FILE TYPE(S): PRG
FILE SIZE: 6.7K
FIRST SEEN: 2025-10-20 14:30:37
APPEARS ON: 1 disk(s)
FILE HASH
cabf3027ce8edc7fe32a3be2d86a05b9e6e63310d91a422a9dd69213a0b9defe
FOUND ON DISKS (1 DISKS)
| DISK TITLE | FILENAME | FILE TYPE | COLLECTION | TRACK | SECTOR | ACTIONS |
|---|---|---|---|---|---|---|
| PB DOMAIN 0001UT | FIREBOLT | PRG | Treasure Chest - Klaus Der Suhler | 21 | 0 | DOWNLOAD FILE |
FILE CONTENT & ANALYSIS
> DETECTED: COMMODORE BASIC PROGRAM (LOAD ADDRESS $0801)
00000000: 01 08 1A 08 0A 00 86 20 41 24 28 38 29 2C 42 24 |....... A$(8),B$|
00000010: 28 39 29 2C 43 24 28 33 30 29 00 65 08 14 00 99 |(9),C$(30).e....|
00000020: 20 22 50 52 4F 47 52 41 4D 20 42 41 52 2F 52 57 | "PROGRAM BAR/RW|
00000030: 53 2F 52 56 50 2F 30 30 31 2E 20 54 48 49 53 20 |S/RVP/001. THIS |
00000040: 50 52 4F 47 52 41 4D 20 57 49 4C 4C 20 43 4F 4D |PROGRAM WILL COM|
00000050: 50 55 54 45 20 54 48 45 20 4C 4F 43 41 54 49 4F |PUTE THE LOCATIO|
00000060: 4E 20 4F 46 22 00 AC 08 1E 00 99 20 22 43 45 4E |N OF"...... "CEN|
00000070: 54 45 52 20 4F 46 20 47 52 41 56 49 54 59 20 46 |TER OF GRAVITY F|
00000080: 4F 52 20 4D 4F 53 54 20 43 4F 4E 56 45 4E 54 49 |OR MOST CONVENTI|
00000090: 4F 4E 41 4C 20 4F 52 20 43 41 4E 41 52 44 20 44 |ONAL OR CANARD D|
000000A0: 45 53 49 47 4E 20 4D 4F 44 45 4C 22 00 F8 08 28 |ESIGN MODEL"...(|
000000B0: 00 99 20 22 41 49 52 43 52 41 46 54 2E 20 49 4E |.. "AIRCRAFT. IN|
000000C0: 20 41 44 44 49 54 49 4F 4E 2C 20 49 54 20 57 49 | ADDITION, IT WI|
000000D0: 4C 4C 20 46 49 4E 44 20 41 45 52 4F 44 59 4E 41 |LL FIND AERODYNA|
000000E0: 4D 49 43 20 43 45 4E 54 45 52 53 20 4F 46 20 53 |MIC CENTERS OF S|
000000F0: 55 52 46 41 43 45 53 22 00 3D 09 32 00 99 20 22 |URFACES".=.2.. "|
00000100: 26 20 49 4E 44 49 43 41 54 45 20 49 46 20 54 48 |& INDICATE IF TH|
00000110: 45 20 56 45 52 54 49 43 41 4C 20 53 54 41 42 49 |E VERTICAL STABI|
00000120: 4C 49 5A 45 52 20 41 52 45 41 20 4F 46 20 43 41 |LIZER AREA OF CA|
00000130: 4E 41 52 44 20 44 45 53 49 47 4E 53 22 00 80 09 |NARD DESIGNS"...|
00000140: 3C 00 99 20 22 49 53 20 4F 46 20 41 44 45 51 55 |<.. "IS OF ADEQU|
00000150: 41 54 45 20 53 49 5A 45 2E 20 4F 54 48 45 52 20 |ATE SIZE. OTHER |
00000160: 46 45 41 54 55 52 45 53 20 50 52 4F 56 49 44 45 |FEATURES PROVIDE|
00000170: 20 20 57 49 4E 47 20 4C 4F 41 44 49 4E 47 2C 22 | WING LOADING,"|
00000180: 00 B5 09 46 00 99 20 22 45 4E 47 49 4E 45 20 50 |...F.. "ENGINE P|
00000190: 4F 57 45 52 20 4C 4F 41 44 49 4E 47 2C 20 41 4E |OWER LOADING, AN|
000001A0: 44 20 41 52 45 41 53 20 4F 46 20 53 55 52 46 41 |D AREAS OF SURFA|
000001B0: 43 45 53 2E 22 00 E6 09 50 00 99 20 22 57 52 49 |CES."...P.. "WRI|
000001C0: 54 54 45 4E 20 42 59 20 42 45 52 4E 49 45 20 52 |TTEN BY BERNIE R|
000001D0: 41 41 44 20 41 4E 44 20 44 49 43 4B 20 53 41 52 |AAD AND DICK SAR|
000001E0: 50 4F 4C 55 53 22 00 12 0A 55 00 99 20 22 52 45 |POLUS"...U.. "RE|
000001F0: 57 52 49 54 54 45 4E 20 46 4F 52 20 43 36 34 20 |WRITTEN FOR C64 |
00000200: 42 59 20 46 52 45 44 20 48 2E 20 4B 52 41 4D 45 |BY FRED H. KRAME|
00000210: 52 22 00 32 0A 5A 00 99 20 22 4D 4F 44 45 4C 20 |R".2.Z.. "MODEL |
00000220: 44 45 53 49 47 4E 41 54 49 4F 4E 22 3B 3A 85 20 |DESIGNATION";:. |
00000230: 43 24 00 38 0A 64 00 99 00 42 0A 69 00 9F 20 31 |C$.8.d...B.i.. 1|
00000240: 2C 34 00 89 0A 6E 00 99 20 22 2A 2A 2A 2A 2A 2A |,4...n.. "******|
00000250: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000260: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000270: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000280: 2A 2A 2A 2A 2A 2A 2A 2A 22 00 D1 0A 73 00 98 31 |********"...s..1|
00000290: 2C 22 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |,"**************|
000002A0: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
000002B0: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
000002C0: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
000002D0: 22 00 E0 0A 78 00 99 20 54 41 42 32 30 2C 43 24 |"...x.. TAB20,C$|
000002E0: 00 F0 0A 7D 00 98 31 2C 54 41 42 32 30 2C 43 24 |...}..1,TAB20,C$|
000002F0: 00 37 0B 82 00 99 20 22 2A 2A 2A 2A 2A 2A 2A 2A |.7.... "********|
00000300: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000310: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000320: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000330: 2A 2A 2A 2A 2A 2A 22 00 7F 0B 87 00 98 31 2C 22 |******"......1,"|
00000340: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000350: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000360: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A |****************|
00000370: 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 2A 22 00 |**************".|
00000380: 85 0B 8C 00 99 00 A2 0B 96 00 99 20 22 54 4F 54 |........... "TOT|
00000390: 41 4C 20 57 49 4E 47 53 50 41 4E 22 3B 3A 85 20 |AL WINGSPAN";:. |
000003A0: 42 34 00 C0 0B A0 00 99 20 22 57 49 4E 47 20 52 |B4...... "WING R|
000003B0: 4F 4F 54 20 43 48 4F 52 44 22 3B 3A 85 20 52 31 |OOT CHORD";:. R1|
000003C0: 00 DD 0B AA 00 99 20 22 57 49 4E 47 20 54 49 50 |...... "WING TIP|
000003D0: 20 43 48 4F 52 44 22 3B 3A 85 20 54 31 00 09 0C | CHORD";:. T1...|
000003E0: B4 00 99 20 22 4C 45 41 44 20 45 44 47 45 20 53 |... "LEAD EDGE S|
000003F0: 57 45 45 50 28 46 57 44 3D 2D 3B 42 4B 57 44 3D |WEEP(FWD=-;BKWD=|
00000400: 2B 29 22 3B 3A 85 20 44 31 00 2E 0C BE 00 99 20 |+)";:. D1...... |
00000410: 22 48 4F 52 49 5A 2E 53 54 41 42 2E 20 54 4F 54 |"HORIZ.STAB. TOT|
00000420: 41 4C 20 53 50 41 4E 22 3B 3A 85 20 42 35 00 52 |AL SPAN";:. B5.R|
00000430: 0C C8 00 99 20 22 53 54 41 42 49 4C 49 5A 45 52 |.... "STABILIZER|
00000440: 20 52 4F 4F 54 20 43 48 4F 52 44 22 3B 3A 85 20 | ROOT CHORD";:. |
00000450: 52 32 00 75 0C D2 00 99 20 22 53 54 41 42 49 4C |R2.u.... "STABIL|
00000460: 49 5A 45 52 20 54 49 50 20 43 48 4F 52 44 22 3B |IZER TIP CHORD";|
00000470: 3A 85 20 54 32 00 A1 0C DC 00 99 20 22 4C 45 41 |:. T2...... "LEA|
00000480: 44 20 45 44 47 45 20 53 57 45 45 50 28 46 57 44 |D EDGE SWEEP(FWD|
00000490: 3D 2D 3B 42 4B 57 44 3D 2B 29 22 3B 3A 85 20 44 |=-;BKWD=+)";:. D|
000004A0: 32 00 C4 0C E6 00 99 20 22 4E 55 4D 42 45 52 20 |2...... "NUMBER |
000004B0: 4F 46 20 56 45 52 54 2E 20 46 49 4E 53 22 3B 3A |OF VERT. FINS";:|
000004C0: 85 20 56 32 00 D5 0C F0 00 8B 20 56 32 B2 30 20 |. V2...... V2.0 |
000004D0: A7 20 33 30 30 00 F4 0C FA 00 99 20 22 56 45 52 |. 300...... "VER|
000004E0: 54 2E 20 46 49 4E 20 48 45 49 47 48 54 22 3B 3A |T. FIN HEIGHT";:|
000004F0: 85 20 42 33 00 17 0D 04 01 99 20 22 56 45 52 54 |. B3...... "VERT|
00000500: 2E 20 46 49 4E 20 52 4F 4F 54 20 43 48 4F 52 44 |. FIN ROOT CHORD|
00000510: 22 3B 3A 85 20 52 33 00 39 0D 0E 01 99 20 22 56 |";:. R3.9.... "V|
00000520: 45 52 54 2E 20 46 49 4E 20 54 49 50 20 43 48 4F |ERT. FIN TIP CHO|
00000530: 52 44 22 3B 3A 85 20 54 33 00 65 0D 18 01 99 20 |RD";:. T3.e.... |
00000540: 22 4C 45 41 44 20 45 44 47 45 20 53 57 45 45 50 |"LEAD EDGE SWEEP|
00000550: 28 46 57 44 3D 2D 3B 42 4B 57 44 3D 2B 29 22 3B |(FWD=-;BKWD=+)";|
00000560: 3A 85 20 44 33 00 8D 0D 22 01 99 20 22 46 49 4E |:. D3...".. "FIN|
00000570: 20 4F 46 46 53 45 54 20 46 52 4F 4D 20 57 49 4E | OFFSET FROM WIN|
00000580: 47 20 4C 2E 45 2E 22 3B 3A 85 20 4C 33 00 BA 0D |G L.E.";:. L3...|
00000590: 2C 01 99 20 22 45 4E 54 45 52 20 32 20 46 4F 52 |,.. "ENTER 2 FOR|
000005A0: 20 43 41 4E 41 52 44 2C 20 31 20 46 4F 52 20 4F | CANARD, 1 FOR O|
000005B0: 54 48 45 52 22 3B 3A 85 20 43 00 E7 0D 36 01 99 |THER";:. C...6..|
000005C0: 20 22 44 49 53 54 2E 20 42 45 54 2E 20 48 20 53 | "DIST. BET. H S|
000005D0: 54 41 42 20 26 20 57 49 4E 47 20 52 4F 4F 54 53 |TAB & WING ROOTS|
000005E0: 22 3B 3A 85 20 4C 31 00 0B 0E 40 01 99 20 22 54 |";:. L1...@.. "T|
000005F0: 4F 54 41 4C 20 57 45 49 47 48 54 20 28 30 55 4E |OTAL WEIGHT (0UN|
00000600: 43 45 53 29 22 3B 3A 85 20 57 31 00 32 0E 4A 01 |CES)";:. W1.2.J.|
00000610: 99 20 22 45 4E 47 49 4E 45 20 53 49 5A 45 20 28 |. "ENGINE SIZE (|
00000620: 43 55 42 49 43 20 49 4E 43 48 29 22 3B 3A 85 20 |CUBIC INCH)";:. |
00000630: 45 39 00 3E 0E 54 01 42 31 B2 42 34 AD 32 00 4A |E9.>.T.B1.B4.2.J|
00000640: 0E 5E 01 42 32 B2 42 35 AD 32 00 61 0E 68 01 45 |.^.B2.B5.2.a.h.E|
00000650: 31 B2 52 31 AE 32 AA 52 31 AC 54 31 AA 54 31 AE |1.R1.2.R1.T1.T1.|
00000660: 32 00 78 0E 72 01 45 32 B2 52 32 AE 32 AA 52 32 |2.x.r.E2.R2.2.R2|
00000670: AC 54 32 AA 54 32 AE 32 00 85 0E 7C 01 47 31 B2 |.T2.T2.2...|.G1.|
00000680: 52 31 AA 54 31 00 92 0E 86 01 47 32 B2 52 32 AA |R1.T1.....G2.R2.|
00000690: 54 32 00 A1 0E 90 01 48 31 B2 52 31 AA 32 AC 54 |T2.....H1.R1.2.T|
000006A0: 31 00 B0 0E 9A 01 48 32 B2 52 32 AA 32 AC 54 32 |1.....H2.R2.2.T2|
000006B0: 00 CA 0E A4 01 58 31 B2 45 31 AD 47 31 AD 36 AA |.....X1.E1.G1.6.|
000006C0: 44 31 AD 33 AC 48 31 AD 47 31 00 E4 0E AE 01 58 |D1.3.H1.G1.....X|
000006D0: 32 B2 45 32 AD 47 32 AD 36 AA 44 32 AD 33 AC 48 |2.E2.G2.6.D2.3.H|
000006E0: 32 AD 47 32 00 F5 0E B8 01 8B 20 56 32 B2 30 20 |2.G2...... V2.0 |
000006F0: A7 20 34 39 30 00 0C 0F C2 01 45 33 B2 52 33 AE |. 490.....E3.R3.|
00000700: 32 AA 52 33 AC 54 33 AA 54 33 AE 32 00 19 0F CC |2.R3.T3.T3.2....|
00000710: 01 47 33 B2 52 33 AA 54 33 00 28 0F D6 01 48 33 |.G3.R3.T3.(...H3|
00000720: B2 52 33 AA 32 AC 54 33 00 42 0F E0 01 58 33 B2 |.R3.2.T3.B...X3.|
00000730: 45 33 AD 47 33 AD 36 AA 44 33 AD 33 AC 48 33 AD |E3.G3.6.D3.3.H3.|
00000740: 47 33 00 51 0F EA 01 53 31 B2 42 31 AD 32 AC 47 |G3.Q...S1.B1.2.G|
00000750: 31 00 60 0F F4 01 53 32 B2 42 32 AD 32 AC 47 32 |1.`...S2.B2.2.G2|
00000760: 00 71 0F FE 01 8B 20 56 32 B2 30 20 A7 20 35 33 |.q.... V2.0 . 53|
00000770: 30 00 80 0F 08 02 53 33 B2 42 33 AD 32 AC 47 33 |0.....S3.B3.2.G3|
00000780: 00 92 0F 12 02 4C B2 58 31 AB 58 32 AA 4C 31 AA |.....L.X1.X2.L1.|
00000790: 52 32 00 9F 0F 1C 02 4C 37 B2 57 31 AD 45 39 00 |R2.....L7.W1.E9.|
000007A0: AF 0F 26 02 8B 20 43 B2 31 20 A7 20 36 31 30 00 |..&.. C.1 . 610.|
000007B0: C6 0F 30 02 50 B2 4C AC 53 32 AD 53 31 AB 45 31 |..0.P.L.S2.S1.E1|
000007C0: AD 31 35 AD 47 31 00 DB 0F 3A 02 4C 38 B2 57 31 |.15.G1...:.L8.W1|
000007D0: AC 37 32 AD 28 53 31 AA 53 32 29 00 EB 0F 44 02 |.72.(S1.S2)...D.|
000007E0: 4C 36 B2 57 31 AC 37 32 AD 53 31 00 FC 0F 4E 02 |L6.W1.72.S1...N.|
000007F0: 8B 20 56 32 B2 30 20 A7 20 36 36 30 00 06 10 58 |. V2.0 . 660...X|
00000800: 02 89 20 36 34 30 00 1F 10 62 02 50 B2 4C AC 53 |.. 640...b.P.L.S|
00000810: 32 AD 53 31 AD 33 AB 45 31 AD 31 35 AD 47 31 00 |2.S1.3.E1.15.G1.|
00000820: 2F 10 6C 02 4C 38 B2 57 31 AC 37 32 AD 53 31 00 |/.l.L8.W1.72.S1.|
00000830: 3F 10 76 02 8B 20 43 B2 31 20 A7 20 36 36 30 00 |?.v.. C.1 . 660.|
00000840: 50 10 80 02 46 B2 50 AA 4C 33 AA 58 33 AB 58 31 |P...F.P.L3.X3.X1|
00000850: 00 69 10 8A 02 56 B2 33 AC 42 31 AC 53 31 AD 28 |.i...V.3.B1.S1.(|
00000860: 31 30 30 AC 46 AC 53 33 29 00 6F 10 94 02 99 00 |100.F.S3).o.....|
00000870: 76 10 99 02 98 31 00 8F 10 9E 02 99 20 54 41 42 |v....1...... TAB|
00000880: 32 30 2C 22 49 4E 50 55 54 20 44 41 54 41 22 00 |20,"INPUT DATA".|
00000890: A9 10 A3 02 98 31 2C 54 41 42 32 30 2C 22 49 4E |.....1,TAB20,"IN|
000008A0: 50 55 54 20 44 41 54 41 22 00 C2 10 A8 02 99 20 |PUT DATA"...... |
000008B0: 54 41 42 32 30 2C 22 3D 3D 3D 3D 3D 20 3D 3D 3D |TAB20,"===== ===|
000008C0: 3D 22 00 DC 10 AD 02 98 31 2C 54 41 42 32 30 2C |="......1,TAB20,|
000008D0: 22 3D 3D 3D 3D 3D 20 3D 3D 3D 3D 22 00 E2 10 B2 |"===== ===="....|
000008E0: 02 99 00 E9 10 B7 02 98 31 00 0D 11 BC 02 99 20 |........1...... |
000008F0: 22 4D 41 49 4E 20 57 49 4E 47 20 44 49 4D 45 4E |"MAIN WING DIMEN|
00000900: 53 49 4F 4E 53 20 28 49 4E 43 48 29 22 00 32 11 |SIONS (INCH)".2.|
00000910: C1 02 98 31 2C 22 4D 41 49 4E 20 57 49 4E 47 20 |...1,"MAIN WING |
00000920: 44 49 4D 45 4E 53 49 4F 4E 53 20 28 49 4E 43 48 |DIMENSIONS (INCH|
00000930: 29 22 00 56 11 C6 02 99 20 22 2D 2D 2D 2D 20 2D |)".V.... "---- -|
00000940: 2D 2D 2D 20 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 20 2D |--- ---------- -|
00000950: 2D 2D 2D 2D 2D 22 00 7B 11 CB 02 98 31 2C 22 2D |-----".{....1,"-|
00000960: 2D 2D 2D 20 2D 2D 2D 2D 20 2D 2D 2D 2D 2D 2D 2D |--- ---- -------|
00000970: 2D 2D 2D 20 2D 2D 2D 2D 2D 2D 22 00 92 11 D0 02 |--- ------".....|
00000980: 99 20 22 54 4F 54 41 4C 20 53 50 41 4E 20 3D 22 |. "TOTAL SPAN ="|
00000990: 42 34 00 AA 11 D5 02 98 31 2C 22 54 4F 54 41 4C |B4......1,"TOTAL|
000009A0: 20 53 50 41 4E 20 3D 22 42 34 00 C6 11 DA 02 99 | SPAN ="B4......|
000009B0: 20 22 57 49 4E 47 20 52 4F 4F 54 20 43 48 4F 52 | "WING ROOT CHOR|
000009C0: 44 20 3D 22 52 31 00 E3 11 DF 02 98 31 2C 22 57 |D ="R1......1,"W|
000009D0: 49 4E 47 20 52 4F 4F 54 20 43 48 4F 52 44 20 3D |ING ROOT CHORD =|
000009E0: 22 52 31 00 FE 11 E4 02 99 20 22 57 49 4E 47 20 |"R1...... "WING |
000009F0: 54 49 50 20 43 48 4F 52 44 20 3D 22 54 31 00 1A |TIP CHORD ="T1..|
00000A00: 12 E9 02 98 31 2C 22 57 49 4E 47 20 54 49 50 20 |....1,"WING TIP |
00000A10: 43 48 4F 52 44 20 3D 22 54 31 00 40 12 EE 02 99 |CHORD ="T1.@....|
00000A20: 20 22 4C 45 41 44 20 45 44 47 45 20 54 49 50 2F | "LEAD EDGE TIP/|
00000A30: 52 4F 4F 54 20 4F 46 46 53 45 54 20 3D 22 44 31 |ROOT OFFSET ="D1|
00000A40: 00 67 12 F3 02 98 31 2C 22 4C 45 41 44 20 45 44 |.g....1,"LEAD ED|
00000A50: 47 45 20 54 49 50 2F 52 4F 4F 54 20 4F 46 46 53 |GE TIP/ROOT OFFS|
00000A60: 45 54 20 3D 22 44 31 00 6D 12 F8 02 99 00 74 12 |ET ="D1.m.....t.|
00000A70: FD 02 98 31 00 A4 12 02 03 99 20 22 48 4F 52 49 |...1...... "HORI|
00000A80: 5A 4F 4E 54 41 4C 20 53 54 41 42 49 4C 49 5A 45 |ZONTAL STABILIZE|
00000A90: 52 20 44 49 4D 45 4E 53 49 4F 4E 53 20 28 49 4E |R DIMENSIONS (IN|
00000AA0: 43 48 29 22 00 D5 12 07 03 98 31 2C 22 48 4F 52 |CH)"......1,"HOR|
00000AB0: 49 5A 4F 4E 54 41 4C 20 53 54 41 42 49 4C 49 5A |IZONTAL STABILIZ|
00000AC0: 45 52 20 44 49 4D 45 4E 53 49 4F 4E 53 20 28 49 |ER DIMENSIONS (I|
00000AD0: 4E 43 48 29 22 00 05 13 0C 03 99 20 22 2D 2D 2D |NCH)"...... "---|
00000AE0: 2D 2D 2D 2D 2D 2D 2D 20 2D 2D 2D 2D 2D 2D 2D 2D |------- --------|
00000AF0: 2D 2D 20 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 20 2D 2D |-- ---------- --|
00000B00: 2D 2D 2D 2D 22 00 36 13 11 03 98 31 2C 22 2D 2D |----".6....1,"--|
00000B10: 2D 2D 2D 2D 2D 2D 2D 2D 20 2D 2D 2D 2D 2D 2D 2D |-------- -------|
00000B20: 2D 2D 2D 20 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 20 2D |--- ---------- -|
00000B30: 2D 2D 2D 2D 2D 22 00 4D 13 16 03 99 20 22 54 4F |-----".M.... "TO|
00000B40: 54 41 4C 20 53 50 41 4E 20 3D 22 42 35 00 65 13 |TAL SPAN ="B5.e.|
00000B50: 1B 03 98 31 2C 22 54 4F 54 41 4C 20 53 50 41 4E |...1,"TOTAL SPAN|
00000B60: 20 3D 22 42 35 00 7C 13 20 03 99 20 22 52 4F 4F | ="B5.|. .. "ROO|
00000B70: 54 20 43 48 4F 52 44 20 3D 22 52 32 00 94 13 25 |T CHORD ="R2...%|
00000B80: 03 98 31 2C 22 52 4F 4F 54 20 43 48 4F 52 44 20 |..1,"ROOT CHORD |
00000B90: 3D 22 52 32 00 AA 13 2A 03 99 20 22 54 49 50 20 |="R2...*.. "TIP |
00000BA0: 43 48 4F 52 44 20 3D 22 54 32 00 C1 13 2F 03 98 |CHORD ="T2.../..|
00000BB0: 31 2C 22 54 49 50 20 43 48 4F 52 44 20 3D 22 54 |1,"TIP CHORD ="T|
00000BC0: 32 00 E7 13 34 03 99 20 22 4C 45 41 44 20 45 44 |2...4.. "LEAD ED|
00000BD0: 47 45 20 54 49 50 2F 52 4F 4F 54 20 4F 46 46 53 |GE TIP/ROOT OFFS|
00000BE0: 45 54 20 3D 22 44 32 00 0E 14 39 03 98 31 2C 22 |ET ="D2...9..1,"|
00000BF0: 4C 45 41 44 20 45 44 47 45 20 54 49 50 2F 52 4F |LEAD EDGE TIP/RO|
00000C00: 4F 54 20 4F 46 46 53 45 54 20 3D 22 44 32 00 47 |OT OFFSET ="D2.G|
00000C10: 14 3E 03 99 20 22 4C 45 4E 47 54 48 20 4F 46 20 |.>.. "LENGTH OF |
00000C20: 46 55 53 45 4C 41 47 45 20 42 45 54 57 45 45 4E |FUSELAGE BETWEEN|
00000C30: 20 57 49 4E 47 20 26 20 53 54 41 42 49 4C 49 5A | WING & STABILIZ|
00000C40: 45 52 20 3D 22 4C 31 00 81 14 43 03 98 31 2C 22 |ER ="L1...C..1,"|
00000C50: 4C 45 4E 47 54 48 20 4F 46 20 46 55 53 45 4C 41 |LENGTH OF FUSELA|
00000C60: 47 45 20 42 45 54 57 45 45 4E 20 57 49 4E 47 20 |GE BETWEEN WING |
00000C70: 26 20 53 54 41 42 49 4C 49 5A 45 52 20 3D 22 4C |& STABILIZER ="L|
00000C80: 31 00 87 14 48 03 99 00 8E 14 4D 03 98 31 00 A0 |1...H.....M..1..|
00000C90: 14 52 03 8B 20 56 32 B2 30 20 A7 20 31 30 30 30 |.R.. V2.0 . 1000|
00000CA0: 00 C7 14 5C 03 99 20 22 56 45 52 54 49 43 4C 45 |...\.. "VERTICLE|
00000CB0: 20 46 49 4E 20 44 49 4D 45 4E 53 49 4F 4E 53 20 | FIN DIMENSIONS |
00000CC0: 28 49 4E 43 48 29 22 00 EF 14 61 03 98 31 2C 22 |(INCH)"...a..1,"|
00000CD0: 56 45 52 54 49 43 4C 45 20 46 49 4E 20 44 49 4D |VERTICLE FIN DIM|
00000CE0: 45 4E 53 49 4F 4E 53 20 28 49 4E 43 48 29 22 00 |ENSIONS (INCH)".|
00000CF0: 16 15 66 03 99 20 22 2D 2D 2D 2D 2D 2D 2D 2D 20 |..f.. "-------- |
00000D00: 2D 2D 2D 20 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 20 2D |--- ---------- -|
00000D10: 2D 2D 2D 2D 2D 22 00 3E 15 6B 03 98 31 2C 22 2D |-----".>.k..1,"-|
00000D20: 2D 2D 2D 2D 2D 2D 2D 20 2D 2D 2D 20 2D 2D 2D 2D |------- --- ----|
00000D30: 2D 2D 2D 2D 2D 2D 20 2D 2D 2D 2D 2D 2D 22 00 4F |------ ------".O|
00000D40: 15 70 03 8B 20 56 32 B2 31 20 A7 20 39 31 30 00 |.p.. V2.1 . 910.|
00000D50: 73 15 7A 03 99 20 22 54 48 45 52 45 20 41 52 45 |s.z.. "THERE ARE|
00000D60: 20 22 56 32 22 56 45 52 54 49 43 4C 45 20 46 49 | "V2"VERTICLE FI|
00000D70: 4E 53 22 00 98 15 7F 03 98 31 2C 22 54 48 45 52 |NS"......1,"THER|
00000D80: 45 20 41 52 45 20 22 56 32 22 56 45 52 54 49 43 |E ARE "V2"VERTIC|
00000D90: 4C 45 20 46 49 4E 53 22 00 A2 15 84 03 89 20 39 |LE FINS"...... 9|
00000DA0: 32 30 00 C9 15 8E 03 99 20 22 54 48 45 52 45 20 |20...... "THERE |
00000DB0: 49 53 20 4F 4E 4C 59 20 4F 4E 45 20 56 45 52 54 |IS ONLY ONE VERT|
00000DC0: 49 43 4C 45 20 46 49 4E 22 00 F1 15 93 03 98 31 |ICLE FIN"......1|
00000DD0: 2C 22 54 48 45 52 45 20 49 53 20 4F 4E 4C 59 20 |,"THERE IS ONLY |
00000DE0: 4F 4E 45 20 56 45 52 54 49 43 4C 45 20 46 49 4E |ONE VERTICLE FIN|
00000DF0: 22 00 08 16 98 03 99 20 22 46 49 4E 20 48 45 49 |"...... "FIN HEI|
00000E00: 47 48 54 20 3D 22 42 33 00 20 16 9D 03 98 31 2C |GHT ="B3. ....1,|
00000E10: 22 46 49 4E 20 48 45 49 47 48 54 20 3D 22 42 33 |"FIN HEIGHT ="B3|
00000E20: 00 3B 16 A2 03 99 20 22 46 49 4E 20 52 4F 4F 54 |.;.... "FIN ROOT|
00000E30: 20 43 48 4F 52 44 20 3D 22 52 33 00 57 16 A7 03 | CHORD ="R3.W...|
00000E40: 98 31 2C 22 46 49 4E 20 52 4F 4F 54 20 43 48 4F |.1,"FIN ROOT CHO|
00000E50: 52 44 20 3D 22 52 33 00 71 16 AC 03 99 20 22 46 |RD ="R3.q.... "F|
00000E60: 49 4E 20 54 49 50 20 43 48 4F 52 44 20 3D 22 54 |IN TIP CHORD ="T|
00000E70: 33 00 8C 16 B1 03 98 31 2C 22 46 49 4E 20 54 49 |3......1,"FIN TI|
00000E80: 50 20 43 48 4F 52 44 20 3D 22 54 33 00 B2 16 B6 |P CHORD ="T3....|
00000E90: 03 99 20 22 4C 45 41 44 20 45 44 47 45 20 54 49 |.. "LEAD EDGE TI|
00000EA0: 50 2F 52 4F 4F 54 20 4F 46 46 53 45 54 20 3D 22 |P/ROOT OFFSET ="|
00000EB0: 44 33 00 D9 16 BB 03 98 31 2C 22 4C 45 41 44 20 |D3......1,"LEAD |
00000EC0: 45 44 47 45 20 54 49 50 2F 52 4F 4F 54 20 4F 46 |EDGE TIP/ROOT OF|
00000ED0: 46 53 45 54 20 3D 22 44 33 00 06 17 C0 03 99 20 |FSET ="D3...... |
00000EE0: 22 54 4F 54 41 4C 20 57 45 49 47 48 54 20 4F 46 |"TOTAL WEIGHT OF|
00000EF0: 20 41 49 52 50 4C 41 4E 45 20 3D 22 57 31 22 4F | AIRPLANE ="W1"O|
00000F00: 55 4E 43 45 53 22 00 34 17 C5 03 98 31 2C 22 54 |UNCES".4....1,"T|
00000F10: 4F 54 41 4C 20 57 45 49 47 48 54 20 4F 46 20 41 |OTAL WEIGHT OF A|
00000F20: 49 52 50 4C 41 4E 45 20 3D 22 57 31 22 4F 55 4E |IRPLANE ="W1"OUN|
00000F30: 43 45 53 22 00 59 17 CA 03 99 20 22 45 4E 47 49 |CES".Y.... "ENGI|
00000F40: 4E 45 20 53 49 5A 45 20 3D 22 45 39 22 43 55 42 |NE SIZE ="E9"CUB|
00000F50: 49 43 20 49 4E 43 48 2E 22 00 7E 17 CF 03 98 31 |IC INCH.".~....1|
00000F60: 2C 22 45 4E 47 49 4E 45 20 53 49 5A 45 20 3D 22 |,"ENGINE SIZE ="|
00000F70: 45 39 22 43 55 42 49 43 20 49 4E 43 48 22 00 C2 |E9"CUBIC INCH"..|
00000F80: 17 D4 03 99 20 22 46 49 4E 20 4C 45 41 44 20 45 |.... "FIN LEAD E|
00000F90: 44 47 45 20 4F 46 46 53 45 54 20 52 45 4C 41 54 |DGE OFFSET RELAT|
00000FA0: 49 56 45 20 54 4F 20 57 49 4E 47 20 4C 45 41 44 |IVE TO WING LEAD|
00000FB0: 20 45 44 47 45 20 41 54 20 52 4F 4F 54 20 3D 22 | EDGE AT ROOT ="|
00000FC0: 4C 33 00 07 18 D9 03 98 31 2C 22 46 49 4E 20 4C |L3......1,"FIN L|
00000FD0: 45 41 44 20 45 44 47 45 20 4F 46 46 53 45 54 20 |EAD EDGE OFFSET |
00000FE0: 52 45 4C 41 54 49 56 45 20 54 4F 20 57 49 4E 47 |RELATIVE TO WING|
00000FF0: 20 4C 45 41 44 20 45 44 47 45 20 41 54 20 52 4F | LEAD EDGE AT RO|
00001000: 4F 54 20 3D 22 4C 33 00 12 18 DE 03 89 20 31 30 |OT ="L3...... 10|
00001010: 33 30 00 18 18 E8 03 99 00 1F 18 ED 03 98 31 00 |30............1.|
00001020: 4C 18 F2 03 99 20 22 54 4F 54 41 4C 20 57 45 49 |L.... "TOTAL WEI|
00001030: 47 48 54 20 4F 46 20 41 49 52 50 4C 41 4E 45 20 |GHT OF AIRPLANE |
00001040: 3D 22 57 31 22 4F 55 4E 43 45 53 22 00 7A 18 F7 |="W1"OUNCES".z..|
00001050: 03 98 31 2C 22 54 4F 54 41 4C 20 57 45 49 47 48 |..1,"TOTAL WEIGH|
00001060: 54 20 4F 46 20 41 49 52 50 4C 41 4E 45 20 3D 22 |T OF AIRPLANE ="|
00001070: 57 31 22 4F 55 4E 43 45 53 22 00 9F 18 FC 03 99 |W1"OUNCES"......|
00001080: 20 22 45 4E 47 49 4E 45 20 53 49 5A 45 20 3D 22 | "ENGINE SIZE ="|
00001090: 45 39 22 43 55 42 49 43 20 49 4E 43 48 2E 22 00 |E9"CUBIC INCH.".|
000010A0: C4 18 01 04 98 31 2C 22 45 4E 47 49 4E 45 20 53 |.....1,"ENGINE S|
000010B0: 49 5A 45 20 3D 22 45 39 22 43 55 42 49 43 20 49 |IZE ="E9"CUBIC I|
000010C0: 4E 43 48 22 00 CA 18 06 04 99 00 D1 18 0B 04 98 |NCH"............|
000010D0: 31 00 EB 18 10 04 99 20 54 41 42 32 30 2C 22 4F |1...... TAB20,"O|
000010E0: 55 54 50 55 54 20 44 41 54 41 22 00 06 19 15 04 |UTPUT DATA".....|
000010F0: 98 31 2C 54 41 42 32 30 2C 22 4F 55 54 50 55 54 |.1,TAB20,"OUTPUT|
00001100: 20 44 41 54 41 22 00 20 19 1A 04 99 20 54 41 42 | DATA". .... TAB|
00001110: 32 30 2C 22 3D 3D 3D 3D 3D 3D 20 3D 3D 3D 3D 22 |20,"====== ===="|
00001120: 00 3B 19 1F 04 98 31 2C 54 41 42 32 30 2C 22 3D |.;....1,TAB20,"=|
00001130: 3D 3D 3D 3D 3D 20 3D 3D 3D 3D 22 00 41 19 24 04 |===== ====".A.$.|
00001140: 99 00 48 19 29 04 98 31 00 6D 19 2E 04 99 20 22 |..H.)..1.m.... "|
00001150: 53 55 52 46 41 43 45 20 41 52 45 41 53 20 49 4E |SURFACE AREAS IN|
00001160: 20 53 51 55 41 52 45 20 49 4E 43 48 22 00 93 19 | SQUARE INCH"...|
00001170: 33 04 98 31 2C 22 53 55 52 46 41 43 45 20 41 52 |3..1,"SURFACE AR|
00001180: 45 41 53 20 49 4E 20 53 51 55 41 52 45 20 49 4E |EAS IN SQUARE IN|
00001190: 43 48 22 00 B8 19 35 04 99 20 22 2D 2D 2D 2D 2D |CH"...5.. "-----|
000011A0: 2D 2D 20 2D 2D 2D 2D 2D 20 2D 2D 20 2D 2D 2D 2D |-- ----- -- ----|
000011B0: 2D 2D 20 2D 2D 2D 2D 22 00 DE 19 36 04 98 31 2C |-- ----"...6..1,|
000011C0: 22 2D 2D 2D 2D 2D 2D 2D 20 2D 2D 2D 2D 2D 20 2D |"------- ----- -|
000011D0: 2D 20 2D 2D 2D 2D 2D 2D 20 2D 2D 2D 2D 22 00 F7 |- ------ ----"..|
000011E0: 19 38 04 99 20 22 54 4F 54 41 4C 20 57 49 4E 47 |.8.. "TOTAL WING|
000011F0: 20 3D 22 32 AC 53 31 00 11 1A 3D 04 98 31 2C 22 | ="2.S1...=..1,"|
00001200: 54 4F 54 41 4C 20 57 49 4E 47 20 3D 22 32 AC 53 |TOTAL WING ="2.S|
00001210: 31 00 3B 1A 42 04 99 20 22 54 4F 54 41 4C 20 48 |1.;.B.. "TOTAL H|
00001220: 4F 52 49 5A 4F 4E 54 41 4C 20 53 54 41 42 49 4C |ORIZONTAL STABIL|
00001230: 49 5A 45 52 20 3D 22 32 AC 53 32 00 66 1A 47 04 |IZER ="2.S2.f.G.|
00001240: 98 31 2C 22 54 4F 54 41 4C 20 48 4F 52 49 5A 4F |.1,"TOTAL HORIZO|
00001250: 4E 54 41 4C 20 53 54 41 42 49 4C 49 5A 45 52 20 |NTAL STABILIZER |
00001260: 3D 22 32 AC 53 32 00 78 1A 4C 04 8B 20 56 32 B2 |="2.S2.x.L.. V2.|
00001270: 30 20 A7 20 31 31 32 30 00 9A 1A 56 04 99 20 22 |0 . 1120...V.. "|
00001280: 54 4F 54 41 4C 20 56 45 52 54 49 43 4C 45 20 46 |TOTAL VERTICLE F|
00001290: 49 4E 20 3D 22 56 32 AC 53 33 00 BD 1A 5B 04 98 |IN ="V2.S3...[..|
000012A0: 31 2C 22 54 4F 54 41 4C 20 56 45 52 54 49 43 4C |1,"TOTAL VERTICL|
000012B0: 45 20 46 49 4E 20 3D 22 56 32 AC 53 33 00 C3 1A |E FIN ="V2.S3...|
000012C0: 60 04 99 00 CA 1A 65 04 98 31 00 DA 1A 6A 04 99 |`.....e..1...j..|
000012D0: 20 22 46 49 58 45 44 20 32 22 00 EB 1A 6F 04 98 | "FIXED 2"...o..|
000012E0: 31 2C 22 46 49 58 45 44 20 32 22 00 35 1B 74 04 |1,"FIXED 2".5.t.|
000012F0: 99 20 22 41 45 52 4F 44 59 4E 41 4D 49 43 20 43 |. "AERODYNAMIC C|
00001300: 45 4E 54 45 52 53 20 4F 46 20 53 55 52 46 41 43 |ENTERS OF SURFAC|
00001310: 45 53 20 28 49 4E 43 48 20 46 52 4F 4D 20 4C 45 |ES (INCH FROM LE|
00001320: 41 44 20 45 44 47 45 20 41 54 20 46 55 53 45 4C |AD EDGE AT FUSEL|
00001330: 41 47 45 29 22 00 7F 1B 79 04 98 31 2C 22 41 45 |AGE)"...y..1,"AE|
00001340: 52 4F 44 59 4E 41 4D 49 43 20 43 45 4E 54 45 52 |RODYNAMIC CENTER|
00001350: 53 20 4F 46 20 53 55 52 46 41 43 45 53 20 28 49 |S OF SURFACES (I|
00001360: 4E 43 48 20 46 52 4F 4D 20 4C 45 41 44 20 45 44 |NCH FROM LEAD ED|
00001370: 47 45 20 41 54 20 46 55 53 45 4C 41 47 45 22 00 |GE AT FUSELAGE".|
00001380: C8 1B 7B 04 99 20 22 2D 2D 2D 2D 2D 2D 2D 2D 2D |..{.. "---------|
00001390: 2D 2D 20 2D 2D 2D 2D 2D 2D 2D 20 2D 2D 20 2D 2D |-- ------- -- --|
000013A0: 2D 2D 2D 2D 2D 2D 20 2D 2D 2D 2D 2D 20 2D 2D 2D |------ ----- ---|
000013B0: 2D 20 2D 2D 2D 2D 20 2D 2D 2D 2D 20 2D 2D 20 2D |- ---- ---- -- -|
000013C0: 2D 2D 2D 2D 2D 2D 2D 22 00 12 1C 7C 04 98 31 2C |-------"...|..1,|
000013D0: 22 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 20 2D 2D 2D |"----------- ---|
000013E0: 2D 2D 2D 2D 20 2D 2D 20 2D 2D 2D 2D 2D 2D 2D 2D |---- -- --------|
000013F0: 20 2D 2D 2D 2D 2D 20 2D 2D 2D 2D 20 2D 2D 2D 2D | ----- ---- ----|
00001400: 20 2D 2D 2D 2D 20 2D 2D 20 2D 2D 2D 2D 2D 2D 2D | ---- -- -------|
00001410: 2D 22 00 28 1C 7E 04 99 20 22 57 49 4E 47 20 41 |-".(.~.. "WING A|
00001420: 2E 43 2E 20 3D 22 58 31 00 3F 1C 83 04 98 31 2C |.C. ="X1.?....1,|
00001430: 22 57 49 4E 47 20 41 2E 43 2E 20 3D 22 58 31 00 |"WING A.C. ="X1.|
00001440: 66 1C 88 04 99 20 22 48 4F 52 49 5A 4F 4E 54 41 |f.... "HORIZONTA|
00001450: 4C 20 53 54 41 42 49 4C 49 5A 45 52 20 41 2E 43 |L STABILIZER A.C|
00001460: 2E 20 3D 22 58 32 00 8E 1C 8D 04 98 31 2C 22 48 |. ="X2......1,"H|
00001470: 4F 52 49 5A 4F 4E 54 41 4C 20 53 54 41 42 49 4C |ORIZONTAL STABIL|
00001480: 49 5A 45 52 20 41 2E 43 2E 20 3D 22 58 32 00 A0 |IZER A.C. ="X2..|
00001490: 1C 92 04 8B 20 56 32 B2 30 20 A7 20 31 31 39 30 |.... V2.0 . 1190|
000014A0: 00 BE 1C 9C 04 99 20 22 56 45 52 54 49 43 4C 45 |...... "VERTICLE|
000014B0: 20 46 49 4E 20 41 2E 43 2E 20 3D 22 58 33 00 DD | FIN A.C. ="X3..|
000014C0: 1C A1 04 98 31 2C 22 56 45 52 54 49 43 4C 45 20 |....1,"VERTICLE |
000014D0: 46 49 4E 20 41 2E 43 2E 20 3D 22 58 33 00 E3 1C |FIN A.C. ="X3...|
000014E0: A6 04 99 00 EA 1C AB 04 98 31 00 F0 1C B0 04 99 |.........1......|
000014F0: 00 F7 1C B5 04 98 31 00 08 1D BA 04 8B 20 43 B2 |......1...... C.|
00001500: 31 20 A7 20 31 32 38 30 00 14 1D C4 04 46 31 B2 |1 . 1280.....F1.|
00001510: 50 AB 58 31 00 22 1D CE 04 46 32 B2 46 31 AC 31 |P.X1."...F2.F1.1|
00001520: 2E 32 00 6D 1D D8 04 99 20 22 43 41 4E 41 52 44 |.2.m.... "CANARD|
00001530: 20 44 45 53 49 47 4E 20 43 2E 47 2E 20 49 53 22 | DESIGN C.G. IS"|
00001540: 46 31 22 54 4F 22 46 32 22 49 4E 43 48 20 41 48 |F1"TO"F2"INCH AH|
00001550: 45 41 44 20 4F 46 20 57 49 4E 47 20 4C 2E 45 2E |EAD OF WING L.E.|
00001560: 20 41 54 20 46 55 53 45 4C 41 47 45 22 00 B4 1D | AT FUSELAGE"...|
00001570: DD 04 98 31 2C 22 43 41 4E 41 52 44 20 44 45 53 |...1,"CANARD DES|
00001580: 49 47 4E 20 43 2E 47 2E 20 49 53 22 46 31 22 54 |IGN C.G. IS"F1"T|
00001590: 4F 22 46 32 22 49 4E 43 48 20 41 48 45 41 44 20 |O"F2"INCH AHEAD |
000015A0: 4F 46 20 4C 2E 45 2E 20 41 54 20 46 55 53 45 4C |OF L.E. AT FUSEL|
000015B0: 41 47 45 22 00 ED 1D E2 04 99 20 22 57 49 4E 47 |AGE"...... "WING|
000015C0: 20 4C 4F 41 44 49 4E 47 20 28 49 4E 43 4C 2E 53 | LOADING (INCL.S|
000015D0: 54 41 42 2E 29 20 49 53 22 4C 38 22 4F 5A 2E 2F |TAB.) IS"L8"OZ./|
000015E0: 53 51 55 41 52 45 20 46 4F 4F 54 2E 22 00 27 1E |SQUARE FOOT.".'.|
000015F0: E7 04 98 31 2C 22 57 49 4E 47 20 4C 4F 41 44 49 |...1,"WING LOADI|
00001600: 4E 47 20 28 49 4E 43 4C 2E 53 54 41 42 2E 29 20 |NG (INCL.STAB.) |
00001610: 49 53 22 4C 38 22 4F 5A 2E 2F 53 51 55 41 52 45 |IS"L8"OZ./SQUARE|
00001620: 20 46 4F 4F 54 2E 22 00 60 1E EC 04 99 20 22 57 | FOOT.".`.... "W|
00001630: 49 4E 47 20 4C 4F 41 44 49 4E 47 20 28 45 58 43 |ING LOADING (EXC|
00001640: 4C 2E 53 54 41 42 2E 29 20 49 53 22 4C 36 22 4F |L.STAB.) IS"L6"O|
00001650: 5A 2E 2F 53 51 55 41 52 45 20 46 4F 4F 54 2E 22 |Z./SQUARE FOOT."|
00001660: 00 9A 1E F1 04 98 31 2C 22 57 49 4E 47 20 4C 4F |......1,"WING LO|
00001670: 41 44 49 4E 47 20 28 45 58 43 4C 2E 53 54 41 42 |ADING (EXCL.STAB|
00001680: 2E 29 20 49 53 22 4C 36 22 4F 5A 2E 2F 53 51 55 |.) IS"L6"OZ./SQU|
00001690: 41 52 45 20 46 4F 4F 54 2E 22 00 A5 1E F6 04 89 |ARE FOOT."......|
000016A0: 20 31 33 32 30 00 B1 1E 00 05 46 33 B2 50 AA 58 | 1320.....F3.P.X|
000016B0: 31 00 BF 1E 0A 05 46 34 B2 46 33 AC 30 2E 38 00 |1.....F4.F3.0.8.|
000016C0: F8 1E 1E 05 99 20 22 57 49 4E 47 20 4C 4F 41 44 |..... "WING LOAD|
000016D0: 49 4E 47 20 28 45 58 43 4C 2E 53 54 41 42 2E 29 |ING (EXCL.STAB.)|
000016E0: 20 49 53 22 4C 38 22 4F 5A 2E 2F 53 51 55 41 52 | IS"L8"OZ./SQUAR|
000016F0: 45 20 46 4F 4F 54 2E 22 00 32 1F 23 05 98 31 2C |E FOOT.".2.#..1,|
00001700: 22 57 49 4E 47 20 4C 4F 41 44 49 4E 47 20 28 45 |"WING LOADING (E|
00001710: 58 43 4C 2E 53 54 41 42 2E 29 20 49 53 22 4C 38 |XCL.STAB.) IS"L8|
00001720: 22 4F 5A 2E 2F 53 51 55 41 52 45 20 46 4F 4F 54 |"OZ./SQUARE FOOT|
00001730: 2E 22 00 6C 1F 28 05 99 20 22 45 4E 47 49 4E 45 |.".l.(.. "ENGINE|
00001740: 20 4C 4F 41 44 49 4E 47 20 49 53 22 4C 37 22 4F | LOADING IS"L7"O|
00001750: 5A 2E 2F 43 55 42 49 43 20 49 4E 43 48 20 4F 46 |Z./CUBIC INCH OF|
00001760: 20 45 4E 47 2E 20 44 49 53 50 2E 22 00 A7 1F 2D | ENG. DISP."...-|
00001770: 05 98 31 2C 22 45 4E 47 49 4E 45 20 4C 4F 41 44 |..1,"ENGINE LOAD|
00001780: 49 4E 47 20 49 53 22 4C 37 22 4F 5A 2E 2F 43 55 |ING IS"L7"OZ./CU|
00001790: 42 49 43 20 49 4E 43 48 20 4F 46 20 45 4E 47 2E |BIC INCH OF ENG.|
000017A0: 20 44 49 53 50 2E 22 00 AD 1F 32 05 99 00 B4 1F | DISP."...2.....|
000017B0: 37 05 98 31 00 D0 1F 3C 05 8B 20 28 43 B2 31 29 |7..1...<.. (C.1)|
000017C0: 20 B0 20 28 56 32 B2 30 29 20 A7 20 31 35 35 30 | . (V2.0) . 1550|
000017D0: 00 F1 1F 46 05 99 20 22 54 48 45 20 56 45 45 20 |...F.. "THE VEE |
000017E0: 45 51 55 41 54 49 4F 4E 20 59 49 45 4C 44 53 22 |EQUATION YIELDS"|
000017F0: 56 00 13 20 4B 05 98 31 2C 22 54 48 45 20 56 45 |V.. K..1,"THE VE|
00001800: 45 20 45 51 55 41 54 49 4F 4E 20 59 49 45 4C 44 |E EQUATION YIELD|
00001810: 53 22 56 00 19 20 50 05 99 00 20 20 55 05 98 31 |S"V.. P... U..1|
00001820: 00 32 20 5A 05 8B 20 56 32 B2 31 20 A7 20 31 34 |.2 Z.. V2.1 . 14|
00001830: 31 30 00 49 20 64 05 53 36 B2 33 AC 42 31 AC 53 |10.I d.S6.3.B1.S|
00001840: 31 AD 28 31 30 30 AC 46 29 00 61 20 6E 05 46 36 |1.(100.F).a n.F6|
00001850: B2 33 AC 42 31 AC 53 31 AD 28 31 30 30 AC 53 33 |.3.B1.S1.(100.S3|
00001860: 29 00 6C 20 78 05 89 20 31 34 33 30 00 82 20 82 |).l x.. 1430.. .|
00001870: 05 53 36 B2 33 AC 42 31 AC 53 31 AD 28 35 30 AC |.S6.3.B1.S1.(50.|
00001880: 46 29 00 99 20 8C 05 46 36 B2 33 AC 42 31 AC 53 |F).. ..F6.3.B1.S|
00001890: 31 AD 28 35 30 AC 53 33 29 00 AA 20 96 05 50 39 |1.(50.S3).. ..P9|
000018A0: B2 53 33 AD 53 36 AC 31 30 30 00 C1 20 A0 05 8B |.S3.S6.100.. ...|
000018B0: 20 50 39 20 B1 B2 20 31 30 30 20 A7 20 31 34 37 | P9 .. 100 . 147|
000018C0: 30 00 D2 20 AA 05 41 24 B2 22 53 4D 41 4C 4C 45 |0.. ..A$."SMALLE|
000018D0: 52 22 00 DD 20 B4 05 89 20 31 34 38 30 00 ED 20 |R".. ... 1480.. |
000018E0: BE 05 41 24 B2 22 4C 41 52 47 45 52 22 00 FF 20 |..A$."LARGER".. |
000018F0: C8 05 4C 39 B2 46 36 AB 50 AA 58 31 AB 58 33 00 |..L9.F6.P.X1.X3.|
00001900: 14 21 D2 05 8B 20 4C 39 20 B1 B2 20 30 20 A7 20 |.!... L9 .. 0 . |
00001910: 31 35 32 30 00 26 21 DC 05 42 24 B2 22 41 48 45 |1520.&!..B$."AHE|
00001920: 41 44 20 4F 46 22 00 31 21 E6 05 89 20 31 35 33 |AD OF".1!... 153|
00001930: 30 00 41 21 F0 05 42 24 B2 22 42 45 48 49 4E 44 |0.A!..B$."BEHIND|
00001940: 22 00 89 21 FA 05 99 20 22 56 45 52 54 49 43 4C |"..!... "VERTICL|
00001950: 45 20 46 49 4E 20 41 52 45 41 20 49 53 20 22 41 |E FIN AREA IS "A|
00001960: 24 22 20 54 48 41 4E 20 4E 45 45 44 45 44 2E 20 |$" THAN NEEDED. |
00001970: 53 55 46 46 49 43 49 45 4E 54 20 41 52 45 41 20 |SUFFICIENT AREA |
00001980: 57 4F 55 4C 44 20 42 45 22 00 D2 21 FF 05 98 31 |WOULD BE"..!...1|
00001990: 2C 22 56 45 52 54 49 43 4C 45 20 46 49 4E 20 41 |,"VERTICLE FIN A|
000019A0: 52 45 41 20 49 53 22 20 41 24 20 22 54 48 41 4E |REA IS" A$ "THAN|
000019B0: 20 4E 45 45 44 45 44 2E 20 53 55 46 46 49 43 49 | NEEDED. SUFFICI|
000019C0: 45 4E 54 20 41 52 45 41 20 57 4F 55 4C 44 20 42 |ENT AREA WOULD B|
000019D0: 45 22 00 1A 22 04 06 99 20 28 31 30 30 AC 53 36 |E".."... (100.S6|
000019E0: AD 53 33 29 22 25 20 4F 46 20 50 52 45 53 45 4E |.S3)"% OF PRESEN|
000019F0: 54 20 44 45 53 49 47 4E 20 4F 52 22 28 56 32 AC |T DESIGN OR"(V2.|
00001A00: 53 36 29 22 53 51 55 41 52 45 20 49 4E 43 48 45 |S6)"SQUARE INCHE|
00001A10: 45 53 20 54 4F 54 41 4C 2E 22 00 62 22 09 06 98 |ES TOTAL.".b"...|
00001A20: 31 2C 28 31 30 30 AC 53 36 AD 53 33 29 22 25 20 |1,(100.S6.S3)"% |
00001A30: 4F 46 20 50 52 45 53 45 4E 54 20 44 45 53 49 47 |OF PRESENT DESIG|
00001A40: 4E 20 4F 52 22 28 56 32 AC 53 36 29 22 53 51 55 |N OR"(V2.S6)"SQU|
00001A50: 41 52 45 20 49 4E 43 48 45 53 20 54 4F 54 41 4C |ARE INCHES TOTAL|
00001A60: 2E 22 00 68 22 0E 06 99 00 6F 22 13 06 98 31 00 |.".h"....o"...1.|
00001A70: 80 22 18 06 99 20 22 53 54 41 4E 44 41 52 44 22 |."... "STANDARD"|
00001A80: 00 92 22 1D 06 98 31 2C 22 53 54 41 4E 44 41 52 |.."...1,"STANDAR|
00001A90: 44 22 00 99 22 1E 06 A0 31 00 9F 22 22 06 80 00 |D".."...1..""...|
00001AA0: 00 00 |.. |
....... A$(8),B$(9),C$(30).E.... "PROGRA
M BAR/RWS/RVP/001. THIS PROGRAM WILL COM
PUTE THE LOCATION OF"...... "CENTER OF G
RAVITY FOR MOST CONVENTIONAL OR CANARD D
ESIGN MODEL"...(.. "AIRCRAFT. IN ADDITIO
N, IT WILL FIND AERODYNAMIC CENTERS OF S
URFACES".=.2.. "& INDICATE IF THE VERTIC
AL STABILIZER AREA OF CANARD DESIGNS"...
<.. "IS OF ADEQUATE SIZE. OTHER FEATURES
PROVIDE WING LOADING,"...F.. "ENGINE P
OWER LOADING, AND AREAS OF SURFACES."...
P.. "WRITTEN BY BERNIE RAAD AND DICK SAR
POLUS"...U.. "REWRITTEN FOR C64 BY FRED
H. KRAMER".2.Z.. "MODEL DESIGNATION";:.
C$.8.D...B.I.. 1,4...N.. "**************
****************************************
********".Q.S..1,"**********************
****************************************
"...X.. TAB20,C$...}..1,TAB20,C$.7.... "
****************************************
**********************".....1,"********
****************************************
**************"............ "TOTAL WINGS
PAN";:. B4... .. "WING ROOT CHORD";:. R1
...... "WING TIP CHORD";:. T1...... "LEA
D EDGE SWEEP(FWD=-;BKWD=+)";:. D1......
"HORIZ.STAB. TOTAL SPAN";:. B5.R.H.. "ST
ABILIZER ROOT CHORD";:. R2.U.R.. "STABIL
IZER TIP CHORD";:. T2...... "LEAD EDGE S
WEEP(FWD=-;BKWD=+)";:. D2.D.... "NUMBER
OF VERT. FINS";:. V2.U.... V2.0 . 300...
... "VERT. FIN HEIGHT";:. B3...... "VERT
. FIN ROOT CHORD";:. R3.9.... "VERT. FIN
TIP CHORD";:. T3.E.... "LEAD EDGE SWEEP
(FWD=-;BKWD=+)";:. D3...".. "FIN OFFSET
FROM WING L.E.";:. L3...,.. "ENTER 2 FOR
CANARD, 1 FOR OTHER";:. C...6.. "DIST.
BET. H STAB & WING ROOTS";:. L1...@.. "T
OTAL WEIGHT (0UNCES)";:. W1.2.J.. "ENGIN
E SIZE (CUBIC INCH)";:. E9.>.T.B1.B4.2.J
.^.B2.B5.2.A.H.E1.R1.2.R1.T1.T1.2.X.R.E2
.R2.2.R2.T2.T2.2...|.G1.R1.T1.....G2.R2.
T2.....H1.R1.2.T1.....H2.R2.2.T2.J...X1.
E1.G1.6.D1.3.H1.G1.....X2.E2.G2.6.D2.3.H
2.G2...... V2.0 . 490...B.E3.R3.2.R3.T3.
T3.2...L.G3.R3.T3.(.V.H3.R3.2.T3.B...X3.
E3.G3.6.D3.3.H3.G3.Q...S1.B1.2.G1.`...S2
.B2.2.G2.Q.... V2.0 . 530.....S3.B3.2.G3
.....L.X1.X2.L1.R2.....L7.W1.E9...&.. C.
1 . 610.F.0.P.L.S2.S1.E1.15.G1...:.L8.W1
.72.(S1.S2)...D.L6.W1.72.S1...N.. V2.0 .
660...X.. 640...B.P.L.S2.S1.3.E1.15.G1.
/.L.L8.W1.72.S1.?.V.. C.1 . 660.P...F.P.
L3.X3.X1.I...V.3.B1.S1.(100.F.S3).O.....
V....1...... TAB20,"INPUT DATA"......1,T
AB20,"INPUT DATA".B.... TAB20,"===== ===
="......1,TAB20,"===== ===="............
1...... "MAIN WING DIMENSIONS (INCH)".2.
A..1,"MAIN WING DIMENSIONS (INCH)".V.F..
"---- ---- ---------- ------".{.K..1,"-
--- ---- ---------- ------"...P.. "TOTAL
SPAN ="B4...U..1,"TOTAL SPAN ="B4.F.Z..
"WING ROOT CHORD ="R1......1,"WING ROOT
CHORD ="R1...... "WING TIP CHORD ="T1..
....1,"WING TIP CHORD ="T1.@.... "LEAD E
DGE TIP/ROOT OFFSET ="D1.G....1,"LEAD ED
GE TIP/ROOT OFFSET ="D1.M.....T....1....
.. "HORIZONTAL STABILIZER DIMENSIONS (IN
CH)".U....1,"HORIZONTAL STABILIZER DIMEN
SIONS (INCH)"...... "---------- --------
-- ---------- ------".6....1,"----------
---------- ---------- ------".M.... "TO
TAL SPAN ="B5.E....1,"TOTAL SPAN ="B5.|.
.. "ROOT CHORD ="R2...%..1,"ROOT CHORD
="R2...*.. "TIP CHORD ="T2.A./..1,"TIP C
HORD ="T2...4.. "LEAD EDGE TIP/ROOT OFFS
ET ="D2...9..1,"LEAD EDGE TIP/ROOT OFFSE
T ="D2.G.>.. "LENGTH OF FUSELAGE BETWEEN
WING & STABILIZER ="L1...C..1,"LENGTH O
F FUSELAGE BETWEEN WING & STABILIZER ="L
1...H.....M..1. .R.. V2.0 . 1000.G.\.. "
VERTICLE FIN DIMENSIONS (INCH)"...A..1,"
VERTICLE FIN DIMENSIONS (INCH)"...F.. "-
------- --- ---------- ------".>.K..1,"-
------- --- ---------- ------".O.P.. V2.
1 . 910.S.Z.. "THERE ARE "V2"VERTICLE FI
NS".....1,"THERE ARE "V2"VERTICLE FINS"
...... 920.I.... "THERE IS ONLY ONE VERT
ICLE FIN"......1,"THERE IS ONLY ONE VERT
ICLE FIN"...... "FIN HEIGHT ="B3. ....1,
"FIN HEIGHT ="B3.;.... "FIN ROOT CHORD =
"R3.W....1,"FIN ROOT CHORD ="R3.Q.... "F
IN TIP CHORD ="T3......1,"FIN TIP CHORD
="T3...... "LEAD EDGE TIP/ROOT OFFSET ="
D3.Y....1,"LEAD EDGE TIP/ROOT OFFSET ="D
3...... "TOTAL WEIGHT OF AIRPLANE ="W1"O
UNCES".4.E..1,"TOTAL WEIGHT OF AIRPLANE
="W1"OUNCES".Y.J.. "ENGINE SIZE ="E9"CUB
IC INCH.".~.O..1,"ENGINE SIZE ="E9"CUBIC
INCH".B.T.. "FIN LEAD EDGE OFFSET RELAT
IVE TO WING LEAD EDGE AT ROOT ="L3...Y..
1,"FIN LEAD EDGE OFFSET RELATIVE TO WING
LEAD EDGE AT ROOT ="L3...... 1030......
......1.L.... "TOTAL WEIGHT OF AIRPLANE
="W1"OUNCES".Z....1,"TOTAL WEIGHT OF AIR
PLANE ="W1"OUNCES"...... "ENGINE SIZE ="
E9"CUBIC INCH.".D....1,"ENGINE SIZE ="E9
"CUBIC INCH".J.....Q....1...... TAB20,"O
UTPUT DATA"......1,TAB20,"OUTPUT DATA".
.... TAB20,"====== ====".;....1,TAB20,"=
===== ====".A.$...H.)..1.M.... "SURFACE
AREAS IN SQUARE INCH"...3..1,"SURFACE AR
EAS IN SQUARE INCH"...5.. "------- -----
-- ------ ----"...6..1,"------- ----- -
- ------ ----"...8.. "TOTAL WING ="2.S1.
..=..1,"TOTAL WING ="2.S1.;.B.. "TOTAL H
ORIZONTAL STABILIZER ="2.S2.F.G..1,"TOTA
L HORIZONTAL STABILIZER ="2.S2.X.L.. V2.
0 . 1120...V.. "TOTAL VERTICLE FIN ="V2.
S3...[..1,"TOTAL VERTICLE FIN ="V2.S3.C.
`...J.E..1.Z.J.. "FIXED 2"...O..1,"FIXED
2".5.T.. "AERODYNAMIC CENTERS OF SURFAC
ES (INCH FROM LEAD EDGE AT FUSELAGE)"..
Y..1,"AERODYNAMIC CENTERS OF SURFACES (I
NCH FROM LEAD EDGE AT FUSELAGE".H.{.. "-
---------- ------- -- -------- ----- ---
- ---- ---- -- --------"...|..1,"-------
---- ------- -- -------- ----- ---- ----
---- -- --------".(.~.. "WING A.C. ="X1
.?....1,"WING A.C. ="X1.F.... "HORIZONTA
L STABILIZER A.C. ="X2......1,"HORIZONTA
L STABILIZER A.C. ="X2. .... V2.0 . 1190
...... "VERTICLE FIN A.C. ="X3......1,"V
ERTICLE FIN A.C. ="X3............1......
......1...... C.1 . 1280...D.F1.P.X1.".N
.F2.F1.1.2.M.X.. "CANARD DESIGN C.G. IS"
F1"TO"F2"INCH AHEAD OF WING L.E. AT FUSE
LAGE"......1,"CANARD DESIGN C.G. IS"F1"T
O"F2"INCH AHEAD OF L.E. AT FUSELAGE"....
.. "WING LOADING (INCL.STAB.) IS"L8"OZ./
SQUARE FOOT.".'....1,"WING LOADING (INCL
.STAB.) IS"L8"OZ./SQUARE FOOT.".`.... "W
ING LOADING (EXCL.STAB.) IS"L6"OZ./SQUAR
E FOOT."......1,"WING LOADING (EXCL.STAB
.) IS"L6"OZ./SQUARE FOOT."...... 1320...
..F3.P.X1.....F4.F3.0.8...... "WING LOAD
ING (EXCL.STAB.) IS"L8"OZ./SQUARE FOOT."
.2.#..1,"WING LOADING (EXCL.STAB.) IS"L8
"OZ./SQUARE FOOT.".L.(.. "ENGINE LOADING
IS"L7"OZ./CUBIC INCH OF ENG. DISP."...-
..1,"ENGINE LOADING IS"L7"OZ./CUBIC INCH
OF ENG. DISP."...2.....7..1.P.<.. (C.1)
. (V2.0) . 1550...F.. "THE VEE EQUATION
YIELDS"V.. K..1,"THE VEE EQUATION YIELD
S"V.. P... U..1.2 Z.. V2.1 . 1410.I D.S
6.3.B1.S1.(100.F).A N.F6.3.B1.S1.(100.S3
).L X.. 1430.. ..S6.3.B1.S1.(50.F).. ..F
6.3.B1.S1.(50.S3).. ..P9.S3.S6.100.A ..
P9 .. 100 . 1470.R ..A$."SMALLER".. ...
1480.. ..A$."LARGER".. H.L9.F6.P.X1.X3.
.!R.. L9 .. 0 . 1520.&!..B$."AHEAD OF".1
!... 1530.A!..B$."BEHIND"..!... "VERTICL
E FIN AREA IS "A$" THAN NEEDED. SUFFICIE
NT AREA WOULD BE".R!...1,"VERTICLE FIN A
REA IS" A$ "THAN NEEDED. SUFFICIENT AREA
WOULD BE".."... (100.S6.S3)"% OF PRESEN
T DESIGN OR"(V2.S6)"SQUARE INCHEES TOTAL
.".B"...1,(100.S6.S3)"% OF PRESENT DESIG
N OR"(V2.S6)"SQUARE INCHES TOTAL.".H"...
.O"...1.."... "STANDARD".."...1,"STANDAR
D"..".. 1.."".....
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