Spin tests of two models of a low-wing monoplane to investigate scale effect in the model test range
National Advisory Committee for Aeronautics, 1941 - Aeronautics - 14 pages
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1/20-scale model spun 15-foot free-spinning wind 30 percent Iy accord when forced added fin area ailerons neutral ailerons set angle of attack angular velocity auxiliary fin changes in scale comparison of figures comparison of results control disposition determining proper model dimensional modifications effect of scale effects of control Elevator angle factors as difficulty fin as shown forced to spin free-spinning wind tunnel full-scale airplane full-scale results horizontal M0DELS mass distribution mean aerodynamic chord model checks model results model test model to spin Model would recover modern low-wing monoplane modifications were indicated moments of inertia NACA Technical Note Normal Flying Condition number of turns oscillates Oscillatory spin percent Figure Qualitative effect Quantitative comparison range of Reynolds rate of descent rates of rotation Recovery not attempted right spine right wing higher rudder 30 scale effect scale model sideslip spun steeper steady-spin parameters tests were performed turns for recovery