Aircraft Performance & DesignMcGraw-Hill Education, 1999 - 580 σελίδες Written by one of the most successful aerospace authors, this new book develops aircraft performance techniques from first principles and applies then to real airplanes. It also address a philosophy of, and techniques for aircraft design. By developing and discussing these two subjects in a single text, the author captures a degree of synergism not found in other texts. The book is written in a conversational style, a trademark of all of John Anderson's texts, to enhance the readers' understanding. |
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aerodynamic center aeronautical aircraft airplane design airplane performance altitude angle of attack aspect ratio Boeing C₁ calculate chapter chord CL)max configuration cruise decreases delta wing drag coefficient drag due drag polar due to lift equation example Figure flap flight path free-stream ft/s fuselage given airplane given by Eq ground roll Gulfstream Gulfstream IV Hence horizontal increase induced drag jet-propelled airplane landing gear lb/ft² leading edge level flight lift coefficient lift slope lift-to-drag ratio Lilienthal load factor Mach number mi/h minimum NACA obtained parasite drag planform pressure propeller-driven airplane propulsive device range rate of climb required curve sea level shown in Fig sketched in Fig specific fuel consumption speed stall straight wing subsonic surface swept wing takeoff thrust required thrust specific fuel transonic turbofan turbojet turboprop variation Vmax wave drag wing loading Wright Flyer zero-lift drag