Data are presented to show the extent to which the maximum lift coefficient and consequently the minimum speed of an airplane, determined by flight tests, may vary with test conditions. The data show that cl-max may vary as much as 14 percent, depending on the altitude and wing loading at which the tests were made, the position or motion of the propeller, and the rate at which the angle of attack is changing when the maximum lift coefficient is obtained. The variation of the maximum lift coefficient with these factors, which are under the control of the test engineer, shows the need of standardizing the test procedure. A further variation is shown with wing conditions as affected by weathering and vibration, factors that cannot be completely controlled.
Flight Tests of an Airplane Showing Dependence of the Maximum Lift Coefficient on the Test Conditions
01.11.1937
Sonstige
Keine Angabe
Englisch
Flight tests of airplane showing dependence of maximum lift coefficient on test conditions
Engineering Index Backfile | 1937
|Comparative flight and full-scale wind-tunnel measurements of maximum lift of airplane
Engineering Index Backfile | 1938
|Comparative flight and full-scale wind tunnel measurements of maximum lift of airplane
Engineering Index Backfile | 1938
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