Aircraft Design: A Conceptual ApproachThis textbook for advanced students focuses on industry design practice rather than theoretical definitions. Covers configuration layout, payload considerations, aerodynamics, propulsion, structure and loads, weights, stability, and control, performance, and cost analysis. Annotation copyright Book |
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Page 96
... approximately 0.85 times the takeoff weight for most fighters . The resulting wing loading is the maximum which will allow the required instantaneous turn . Sustained Turn The sustained turn rate is also important for success in combat ...
... approximately 0.85 times the takeoff weight for most fighters . The resulting wing loading is the maximum which will allow the required instantaneous turn . Sustained Turn The sustained turn rate is also important for success in combat ...
Page 298
... ( approximately = area of shorter wing / area of longer wing ) At supersonic speeds , the drag - due - to - lift factor ( K ) increases substan- tially . In terms of Oswald efficiency factor , e is reduced to approximately 0.3-0.5 at Mach ...
... ( approximately = area of shorter wing / area of longer wing ) At supersonic speeds , the drag - due - to - lift factor ( K ) increases substan- tially . In terms of Oswald efficiency factor , e is reduced to approximately 0.3-0.5 at Mach ...
Page 334
... approximately vertical in the body axis . For a subsonic aircraft , maximum or dive speed is typically 50 % higher than the level - flight cruise speed . For a supersonic aircraft the maximum speed is typically about Mach 0.2 faster ...
... approximately vertical in the body axis . For a subsonic aircraft , maximum or dive speed is typically 50 % higher than the level - flight cruise speed . For a supersonic aircraft the maximum speed is typically about Mach 0.2 faster ...
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Common terms and phrases
actual additional aerodynamic aileron aircraft airfoil allow altitude analysis angle of attack Approach approximately aspect ratio assumed calculated cause Chapter chord climb Conceptual cost cruise curve defined deflection determined developed direction discussed distance distribution drag effect engine equal equations estimated example factor fighter Figure flap flight flow force fraction fuel fuselage gear geometry ground horizontal increase initial inlet landing layout length lift coefficient lift force limit load Mach number material maximum methods mission mounted Note nozzle operating performance pitching position pressure produce propeller range reduced resulting roll SEGMENT selected separation shock shown in Fig shows sizing speed stall stress structural subsonic supersonic surface Table tail takeoff term thrust turn typical usually velocity vertical weight wheel wing wing loading