Aircraft Design Projects Episode 5 pptx

... ft 30 40 50 60 0 –20 –10 10 20 Aircraft speed (m/s) 0 50 100 150 200 250 300 Fig. 5. 19 Aircraft rate of climb 0 50 00 10000 15 000 20000 25 000 30000 35 000 40000 Aircraft altitude (ft) Max. climb rate (m/s) 20 30 40 50 60 0 10 Fig. ... (V = 140 m/s, n = 4.2 g ) 100 50 0 50 –100 – 150 –200 – 250 –300 0 50 100 150 200 250 300 350 400 Fig. 5. 13 Specific excess power at...

Ngày tải lên: 13/08/2014, 15:21

... 6.22 6.6 236 340 0.69 53 6 75 0.16 AR -5 Formula 1 racer 4.42 6.4 5. 12 8.0 1 65 290 0 .57 55 6 49 – Monnett Sonerai Formula V racer 5. 08 5. 08 6.97 3.7 199 340 0 .59 479 45 0. 15 Optiori AirReno Formula ... /S)} 5. 8.6 Combat turn at 25 000 ft This is similar to the analysis above but with α = 0 .55 7/1.2 25 = 0. 455 . At 25 000 ft the best speed for excess power is 200 m/s (i...

Ngày tải lên: 08/08/2014, 11:21

... 4.3.7 Aircraft developments 54 4.3.8 Commercial analysis 55 4.4 Information retrieval 56 4 .5 Design concepts 57 4 .5. 1 Conventional layout(s) 57 4 .5. 2 Braced wing/canard layout 58 4 .5. 3 Three-surface ... objectives 354 11.6.3 Course structure 354 11.6.4 Assessment criteria 355 11.6 .5 Peer review 356 11.7 Naming your aircraft 356 Footnote 357 Appendix A: Units...

Ngày tải lên: 13/08/2014, 15:21

... page 30 — # 25 30 Aircraft Design Projects 58 8 58 4 58 0 0. 25 0.30 Wing taper ratio 0. 35 0 .5% 54 30 54 20 0. 25 0.30 Wing taper ratio Fuel wt (Ib) 0. 35 0 .5% 6.48 6.44 0. 25 0.30 Wing ... 80 PAX 58 00 ft 72 PAX 60 000 60 PAX 52 000 Fig. 2.18 Operational design study – take-off mass (example) Seat mile cost (cents) 5. 15 5. 0 4. 95 4. 85 4....

Ngày tải lên: 13/08/2014, 15:21

... Design Projects 72 70 74 76 78 80 82 8 10 12 14 400 450 50 0 55 0 $1000 Fig. 4. 25 Trade-off study: DOC per flight 48 50 52 54 8 10 12 14 400 450 50 0 55 0 $1000 Fig. 4.26 Trade-off study: cash DOC per ... — 2003/3/10 — page 78 — #33 78 Aircraft Design Projects 450 0.27 0.30 0.32 50 0 Wing loading (W /S ) (kg/m 2 ) 55 0 Thrust loading (T/W ) Original design point New...

Ngày tải lên: 13/08/2014, 15:21

... ratio (7 .5) to provide for a greater fin arm. The ‘conventional’ will have a low aspect ratio (5. 5) to “chap 05 — 2003/3/10 — page 140 — #40 140 Aircraft Design Projects 5. 11 .5 Revised aircraft ... similar to the analysis above but with α = 0 .55 7/1.2 25 = 0. 455 . At 25 000 ft the best speed for excess power is 200 m/s (in SI units) ∴ q = 0 .5 × 0 .55 7 × 200 2 = 11 140 Wit...

Ngày tải lên: 13/08/2014, 15:21

... 2 5. Aesthetics/Noise −21−102−1 Subtotal 1/6 −104276 3 Total −3 .50 2.83 1.00 3 .50 4 .50 −3 .50 “chap06” — 2003/3/10 — page 172 — #30 172 Aircraft Design Projects 30 40 50 60 70 80 90 100 110 Aircraft ... boundary 0 10 20 30 40 50 60 70 80 Max. speed limits (depending on aerodynamic drag and prop. efficiency) Fig. 6. 15 Turn performance 1 .5 2.0 2 .5 3.0 3 .5 4.0 Aircraft...

Ngày tải lên: 13/08/2014, 15:21

... 19.2 Fixed systems 3 673 (8 100) 5. 8 Aircraft empty 25 846 (56 990) 41.1 Crew (two pilots) 50 0 (1 100) Weapons 6 100 (13 450 ) Zero fuel mass 32 446 (71 54 3) 51 .7 Fuel ∗ 30 360 (66 944) 48.3 Max. ... area Opt. alt. M1.6 1000 nm 4 5 Climb to 50 000 ft 5 6 Dash to target 50 000 ft M1.6 750 nm 6–7 Turn and weapon release 50 000 ft 180° 7–8 Dash out 50 000ft M1.6 750 nm 8–9...

Ngày tải lên: 13/08/2014, 15:21

... manoeuvre –300 –200 –100 0 100 200 300 400 50 0 600 700 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8 2 70 70 65 60 55 50 Design req. 50 000 ft 43 36 Alt. (ft × 10 –3 ) 30 65 60 k 55 k 50 k 43 k 36 k 30 k 20 k 10 k 50 00 150 0 SL Conditions Û 1g Û Dry engine thrust ... 8. 25 SEP for M1.6 versus altitude 0.0 0.2 0.4 0.6 0.8 1.0 1.2 Mach number 10 20 1.4 1.6 50 100 150 200 250 300 Max d...

Ngày tải lên: 13/08/2014, 15:21