Aircraft Design Projects Episode 6 pdf

... extent, the Hawk aircraft appear to fit closely to the climb constraint line. This validates this requirement. “chap 06 — 2003/3/10 — page 160 — #18 160 Aircraft Design Projects Aircraft data O/A ... in the ‘disposable’ mass section. Aircraft data O/A length 16. 2 ft /5 m O/A height 4.0 ft /1.25 m Wing span 20 ft /6. 1 Wing area 66 sq. ft /6. 1 sq. m Wing AR 6 Wing taper 0.3 W...

Ngày tải lên: 13/08/2014, 15:21

... page 96 — #51 96 Aircraft Design Projects Table 4.7 Layout Passengers SMC Cash SMC Executive only 80 12.99 8.83 Mixed class 107 9.74 6. 62 Economy only 120 8.70 5.91 Charter only 150 6. 85 4 .68 The ... 96 4 86 lb Still air range 68 10 nm All economy version (120 PAX) Payload 12 160 kg, 26 812 lb Fuel 44 138 kg, 97 324 lb Still air range 66 75 nm Charter version (150 PAX) Pay...

Ngày tải lên: 13/08/2014, 15:21

... 49 76/ 10 970 C Do (×10 4 ) fuselage 26. 9 26. 7 25.2 26. 4 wing 58.3 56. 1 51 .6 55.1 braces 16. 8 16. 4 15.2 16. 2 tail 7.2 7 .6 7.2 7.5 nacelles 9.7 9 .6 9.0 9.4 C Do total basic 119.4 1 16. 4 108.2 114 .6 Add ... 9.18. Altitude km 1.4 4 .6 9.0 14.0 18.0 ft 460 0 15 080 29 500 45 900 59 000 True airspeed m/s 138 163 209 2 06 2 06 kt 268 3 16 4 06 400 400 Drag N 5 362 54 86 5552 3...

Ngày tải lên: 13/08/2014, 15:21

... efficiency) Fig. 6. 15 Turn performance 1.5 2.0 2.5 3.0 3.5 4.0 Aircraft load factor (g ) Bank angle (°) 40 45 50 55 60 65 70 75 80 Fig. 6. 16 Aircraft bank angle (balance turn) versus load factor initial design ... engineering and design $ 168 8 Aircraft production $215 935 Flight test operations $400 Overhead and indirect costs $21 802 Profit $21 802 Total $ 261 62 7 Aircra...

Ngày tải lên: 08/08/2014, 11:21

... layout 60 4.5.5 Configuration selection 61 4 .6 Initial sizing and layout 62 4 .6. 1 Mass estimation 62 4 .6. 2 Engine size and selection 63 4 .6. 3 Wing geometry 63 4 .6. 4 Fuselage geometry 67 4 .6. 5 ... propulsion system 154 6. 5 Design concepts 157 6. 6 Initial sizing 158 6. 6.1 Initial mass estimations 159 6. 6.2 Initial aerodynamic considerations 162 6. 6.3 Propell...

Ngày tải lên: 13/08/2014, 15:21

... — #33 38 Aircraft Design Projects Max. take-off weight (lb) 76 000 1500 nm 68 000 1250 1000 61 00 64 00 80 PAX 5800 ft 72 PAX 60 000 60 PAX 52 000 Fig. 2.18 Operational design study ... 1.35 1.25 1250 5800 61 80 1000 80 PAX 72 PAX 60 PAX 1500 nm 64 00 ft Fig. 2. 16 Operational design study – engine size (example) Gross wing area (sq. ft) 760 68 0 6...

Ngày tải lên: 13/08/2014, 15:21

... = (1/2/3/4/5 /6/ 7/8) (A reminder: 1 m/s is approx. 2 kt (more precisely 1.94).) “chap05” — 2003/3/10 — page 1 16 — # 16 1 16 Aircraft Design Projects Conventional mass estimation = 76 kg, assume ... 288 /63 5 Total propulsion 865 /1907 15.2 Equipment (total) 1200/ 264 6 21.0 Total aircraft empty 3311/7300 58.0 Fuel 900/1984 15.8 Crew 1 36/ 300 Weapon load 1 360 /3000 Total Useful...

Ngày tải lên: 13/08/2014, 15:21

... 1 1 2 Subtotal 1 /6 10 3 8 4 8 9 “chap 06 — 2003/3/10 — page 166 — #24 166 Aircraft Design Projects • Advance ratio 2.0 (racing), 0.5 (take-off). • Efficiency 82 per cent max. 6. 7 Initial performance ... of Four-part telescopic win g Fig. 7.3 Baseline aircraft layout “chap 06 — 2003/3/10 — page 168 — # 26 168 Aircraft Design Projects 30 50 70 90 110 Aircraft speed (m /s) (...

Ngày tải lên: 13/08/2014, 15:21

... structure 10 0 96 (22 262 ) 16. 1 Propulsion system 12 077 ( 26 630) 19.2 Fixed systems 3 67 3 (8 100) 5.8 Aircraft empty 25 8 46 ( 56 990) 41.1 Crew (two pilots) 500 (1 100) Weapons 6 100 (13 450) Zero ... (M TO /S) kg/sq. m 262 – 467 315–544 447–5 16 Thrust/Weight ratio (dry) 0 .65 –1.29 0. 56 0.88 0. 26 0.40 associated with existing aircraft of the same type. It is possible to...

Ngày tải lên: 13/08/2014, 15:21