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airplane angle of attack approximate airfoil boundary calculation camber line Cartesian mapping function Cauchy integral formula chord extensions chordwise circle CMF method COMMITTEE FOR AERONAUTICS CONFIDENTIAL conformal mapping contour corresponding cowl and intercooler curves derived determined drag coefficient effect elevator angle equa extended chord Fi.ed Fourier series fuselage center line given airfoil hinge line hinge-moment coefficient horizontal tail hunting oscillation Inboard afterbodies inboard nacelle increase initial airfoil intercooler flaps closed inverse problem Langley Field leading-edge gloves lift coefficient Mach number maximum metal elevator modified model modified nacelle afterbodies NACA NATIONAL ADVISORY COMMITTEE normal rated power nose obtained prescribed velocity distribution profile drag-lift ratio reference region Reynolds number root chord rotor shown in figure slope stagnation point stall standard and modified Standard configuration standard model straight line tests thin-airfoil theory tion trailing edge trailing-edge angle trailing-edge extensions trailing-edge strips transition fixed turbulence