ReportU.S. Government Printing Office, 1949 - Aeronautics |
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1.2 Lift coefficient 6-series aerodynamic center aerodynamic-center location AMES AERONAUTICAL LABORATORY Angle of attack approximation aspect ratio Wing Center of gravity Change in stabilizer characteristics of model coefficient is given COEFFICIENTS FOR MODEL Comparison of computed computed and experimental computing power-on correlation curves desired propeller downwash angle due Dual rotation due to power effects of power EFFECTS OF PROPELLER elevator hinge line experimental data figure 9 final power-on Hamilton Standard horizontal tail immersed in slipstream increment JOSEPH WEIL Langley Aeronautical Laboratory Langley Field model 21 models 13 normal force parameter pitching pitching moments PITCHING-MOMENT AND LIFT plan form power-off data Power-off test data Propeller diameter PROPELLER OPERATION radians Reynolds number span load distribution stabilizer effectiveness static longitudinal stability tail contribution tail location tail span tail-off thrust coefficient thrust line tilt Wind-tunnel data wing root chord Wing span Wing taper ratio zero lift
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Page 1 - An analysis of these data suggested the possibilities of a semiempirical approach to the problem of determining the effects of power on the tail contribution to stability.