Interrelated effects of Mach and Reynolds numbers on the maximum lift coefficient were investigated and compared with existing pertinent wind- tunnel data. Six pursuit-type airplanes embodying typical conventional and low- drag airfoils were selected, and flight data obtained in gradual stalls were made during turns or pull-ups with airplanes in clean condition over a range of Mach numbers from 0.15 to 0.72 and of Reynolds numbers from 4,400,000 to 19,500, 000. Flight data were plotted and found to correlate closely with available wind-tunnel data.
Effect of Mach and Reynolds Numbers on Maximum Lift Coefficient
1946
40 pages
Report
Keine Angabe
Englisch
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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