Results of wind-tunnel tests of three wing models with various aileron configurations are presented. Density in the range of 0.08 X 10-2 to 0.58 X 10-2 slug per cube- foot has little effect on the initial amplitude or initial Mach number associated with the aileron oscillations (buzz). However, the frequencies decrease somewhat with decrease in den sixty. The initial Mach number associated with buzz decreases with -increasing angle of attack, whereas mass balancing and changes in spring stiffness in these tests have little effect. Increasing the aileron mass moment of inertia lowers the oscillation frequency. Placing the aileron at the wing tip delays the onset of buzz to a higher Mach number. There are experimental indications that the buzz range is limited to a range of Mach numbers above the wing critical Mach number. A comparison of the results of the test data with two previously published empirical analyses is made.
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