Flight tests were conducted on a Bell P-39N-1 airplane to determine the variation with Mach and Reynolds numbers of the maximum lift coefficient obtainable. The tests were made with the propeller in the constant-speed high-pitch setting and with the power off in order to minimize the effect of power and the propeller. The investigation covered a Mach number range of 0.146 to 0.655 and a Reynolds-number range of 4,900,000 to 17,100,000.The results of the investigation indicated that the maximum lift coefficient obtainable decreased markedly with an increase in Mach number for a given Reynolds number and exhibited a tendency to increase with an increase in Reynolds number for a given Mach number up to a Mach number of 0.55.
Effect of Mach and Reynolds Numbers on the Power-Off Maximum Lift Coefficient Obtainable on a P-39N-1 Airplane as Determined in Flight
1944-06-01
Miscellaneous
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English
Effect of Mach and Reynolds numbers on maximum lift coefficient
TIBKAT | 1946
|Effect of Mach and Reynolds numbers on maximum lift coefficient
Engineering Index Backfile | 1946
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