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aerodynamic air flow airfoil angle of attack approximately average stress axis balance chord body of revolution boundary layer brake horsepower buckling stress calculated carburetor characteristics column COMMITTEE FOR AERONAUTICS computed CONFIDENTIAL corresponding cross section curvature curves design charts determined effect Elliptical nose elliptical-nose overhang equation estimated figure 12 flap deflection flap hinge-moment coefficient flight tests force tests free-flight tunnel fuselage gap sealed given gun turret inches increased indicated interference Langley Field length lift coefficient load Mach number maximum measured meridian profile NACA NATIONAL ADVISORY COMMITTEE negative pressure coefficients nose shape oblate spheroid obtained OJ OJ OJ OJ OJOJOJOJOJ OJ Ol OJ rH parameter peaks percent plain flap plotted potential flow pressure distribution protuberance reference rH rH rH root chord Short method shown in figure static margin stiffener strain gages test data theoretical tion two-dimensional unsealed values variation velocity distribution vertical tails wing Z-section