A flight investigation was conducted to determine the contributions of wing, tail, and fuselage to the total airplane lift of a propeller-driven fighter-type airplane. The tests covered a Mach number range from 0.2 to 0.8. The loads on the various airplane components were measured by the use of calibrated strain-gage installations located at the roots of the wings and horizontal tail surfaces.
Flight Determination of Wing and Tail Loads on a Fighter-Type Airplane by Means of Strain-Gage Measurements
1948
24 pages
Report
Keine Angabe
Englisch
Aerodynamics , Fighter aircraft , Measurement , Lift , Aircraft , Tail assemblies , Surfaces , Flight , Installation , Fuselages , Strain gages , Mach number , Wings , Determination , Horizontal stabilizers , Propellers , Aq moo-11-3606
Engineering Index Backfile | 1948
|Engineering Index Backfile | 1949
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