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 228
... wheels in place of the single wheels shown in Fig . 11.1 . As aircraft weights become larger , the required wheel size for a single wheel capable of holding the aircraft's weight becomes too large . Then multiple wheels are used to ...
... wheels in place of the single wheels shown in Fig . 11.1 . As aircraft weights become larger , the required wheel size for a single wheel capable of holding the aircraft's weight becomes too large . Then multiple wheels are used to ...
Page 230
... wheel in the static position assuming an aircraft angle of attack for landing which gives 90 % of the maximum lift . This ranges from about 10-15 deg for most types of aircraft . The " tipback angle " is the maximum aircraft nose - up ...
... wheel in the static position assuming an aircraft angle of attack for landing which gives 90 % of the maximum lift . This ranges from about 10-15 deg for most types of aircraft . The " tipback angle " is the maximum aircraft nose - up ...
Page 231
... wheel is aligned with the nose wheel . For most aircraft this angle should be no greater than 63 deg ( 54 deg for carrier - based aircraft ) . Figure 11.4 also shows the desired strut - travel angle as about 7 deg . This optimal angle ...
... wheel is aligned with the nose wheel . For most aircraft this angle should be no greater than 63 deg ( 54 deg for carrier - based aircraft ) . Figure 11.4 also shows the desired strut - travel angle as about 7 deg . This optimal angle ...
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Common terms and phrases
actual aerodynamic aerodynamic center aileron aircraft design aircraft weight airflow airfoil altitude analysis angle of attack approximately aspect ratio calculated camber canard Chapter chord climb component compression Conceptual Approach conceptual design cost cross section cruise curve deflection determined dihedral duct effect empty weight engine equations estimated fighter flap flight flow force ft² fuel fuselage horizontal tail increase induced drag initial inlet landing gear layout leading edge leading-edge lift coefficient load factor loiter longitudinal Mach number maximum lift methods MISSION SEGMENT NACA nacelle nozzle parasite drag payload pilot pitching pitching moment produce propeller propulsion reduced roll shear shock shown in Fig sizing speed stall static structural subsonic supersonic surface T-tail takeoff weight thrust transonic turbofan turboprop turn rate typical vectoring velocity vertical tail VTOL wave drag weight fraction wetted area wheel wing loading zero