NASA MemorandumNational Aeronautics and Space Administration, 1958 - Aeronautics |
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accuracy Additional Airloads aerodynamic center aerodynamic-influence coefficients Aiken airplane center line angle of attack angle-of-attack distribution Ay/h bending moment CALCULATING STEADY-STATE SPAN Ce,N center of pressure Co,N diagonal matrix downwash control point downwash factor downwash tables dynamic pressure element equations of equilibrium evaluated external store external-store effects final angle FLEXIBLE WINGS ft²-deg inertia loading initial angle initial-angle-of-attack distribution integrating matrix interpolating factor Langley Field lift-curve slope load factor Load on external Load on wing LOADING ON FLEXIBLE matrix inversion MODIFIED MATRIX METHOD NASA MEMO nondimensional number of terms pitching pitching moment premultiplying resulting rigid wing sample problem semispan station shear distribution spanwise steady-state aeroelastic problems STEADY-STATE SPAN LOADING SUBSONIC FLIGHT tables of downwash unit of load values of qmR vortex semispan vortex stations wing angle wing quarter-chord wing station wing twist wing-root angle WINGS IN SUBSONIC XqmR Δη λαμ
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Page 1 - ... CALCULATING STEADY-STATE SPAN LOADING ON FLEXIBLE WINGS IN SUBSONIC FLIGHT By Patrick A. Gainer and William S. Aiken, Jr.