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 49
... chord line is the sweep most related to subsonic flight . It is impor- tant to avoid confusing these two sweep angles . The equation at the bottom of Fig . 4.16 allows converting from one sweep angle to the other . Airfoil pitching ...
... chord line is the sweep most related to subsonic flight . It is impor- tant to avoid confusing these two sweep angles . The equation at the bottom of Fig . 4.16 allows converting from one sweep angle to the other . Airfoil pitching ...
Page 140
... chord ( MAC or C ) , which is mathematically obtained by Eq . ( 7.9 ) . The location of the mean chord is obtained graphically as the intersection of the 50 % -chord line and a line drawn from a point located at the tip chord length ...
... chord ( MAC or C ) , which is mathematically obtained by Eq . ( 7.9 ) . The location of the mean chord is obtained graphically as the intersection of the 50 % -chord line and a line drawn from a point located at the tip chord length ...
Page 146
... CHORD POINTS FROM ( 2A ) AND ( 2B ) 3 - AT ROOT AND TIP , SWING POINTS DOWN ONTO CHORD REFERENCE LINE 4 - CONNECT THE POINTS FROM ( 3 ) 5 - SWING POINT UP TO NEW AIRFOIL LOCATION 6- REPEAT FOR OTHER POINTS ( 1 ) ( 2B ) Fig . 7.30 Wing ...
... CHORD POINTS FROM ( 2A ) AND ( 2B ) 3 - AT ROOT AND TIP , SWING POINTS DOWN ONTO CHORD REFERENCE LINE 4 - CONNECT THE POINTS FROM ( 3 ) 5 - SWING POINT UP TO NEW AIRFOIL LOCATION 6- REPEAT FOR OTHER POINTS ( 1 ) ( 2B ) Fig . 7.30 Wing ...
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Common terms and phrases
actual aerodynamic center aileron aircraft weight airflow airfoil altitude analysis angle of attack approximately aspect ratio axis boundary layer calculated camber canard Chapter chord climb component compression conceptual design conic cross section cruise curve defined deflection determined dihedral duct dynamic pressure effect empty weight engine equations estimated fighter flap flight flow force fuel fuselage geometry horizontal tail increase induced drag initial inlet landing gear layout leading edge leading-edge lift coefficient lift force load factor loiter longitudinal Mach number maximum lift methods mission nacelle nozzle parasite drag pilot pitching pitching moment produce propulsion radar radius reduced roll rudder shear shock shown in Fig span stability static stress structural strut subsonic supersonic surface sweep T-tail tanks thrust tion tire transonic turboprop turn rate typical usually velocity vertical tail wave drag wetted area wheel wing loading zero