Aerodynamics, Aeronautics and Flight MechanicsA single, comprehensive, in-depth treatment of both basic, and applied modern aerodynamics. Covers the fluid mechanics and aerodynamics of incompressible and compressible flows, with particular attention to the prediction of lift and drag characteristics of airfoils and wings and complete airplane configurations. Following an introduction to propellers, piston engines, and turbojet engines, methods are presented for analyzing the performance of an airplane throughout its operating regime. Also covers static and dynamic longitudinal and lateral-directional stability and control. Includes lift, drag, propulsion and stability and control data, numerical methods, and working graphs. |
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Results 1-3 of 84
Page 69
... angle of attack is increased , the flow can separate initially near the trailing edge , with the separation point progressively moving forward as the angle of attack continues to increase . The degree to which the flow separates from ...
... angle of attack is increased , the flow can separate initially near the trailing edge , with the separation point progressively moving forward as the angle of attack continues to increase . The degree to which the flow separates from ...
Page 138
... angle of attack . If we define the angle of attack of the wing to be that of the zero lift line at the root , the angle of attack of the wing for zero lift will be negative ; that is , we must rotate the entire wing nose downward in ...
... angle of attack . If we define the angle of attack of the wing to be that of the zero lift line at the root , the angle of attack of the wing for zero lift will be negative ; that is , we must rotate the entire wing nose downward in ...
Page 283
... angle of attack can cause the wing to bend upward . As it does , because of the sweep , the tips tend to twist more nose downward relative to the rest of the wing . Again , this can produce a nose - up pitching moment that increases the ...
... angle of attack can cause the wing to bend upward . As it does , because of the sweep , the tips tend to twist more nose downward relative to the rest of the wing . Again , this can produce a nose - up pitching moment that increases the ...
Contents
ONE INTRODUCTION 119 | 1 |
TWO FLUID MECHANICS | 16 |
THREE THE GENERATION OF LIFT | 61 |
Copyright | |
11 other sections not shown
Common terms and phrases
aerodynamic center aileron aircraft airplane altitude angle of attack approximately aspect ratio blade boundary layer C₁ calculated camber center of gravity Cherokee 180 chord climb component compressor configuration constant cruise deflected delta wing distance drag coefficient effect engine equal Equation estimated flight flow fluid force form drag free-stream ft² fuel function fuselage given horizontal tail increase increment induced drag interference drag laminar leading edge lift coefficient lift curve lift line Mach number maximum NACA normal parasite drag pictured in Figure planform presented in Figure propeller Reference Reynolds number roll sea level shock wave shown in Figure skin friction slug-ft² speed stability stall static pressure subsonic supersonic surface takeoff temperature thickness thrust trailing edge trim true airspeed turbine turbofan turbojet V₁ velocity vertical tail vortex weight winglet yawing zero lift