Report on flight tests to determine scale and compressibility effects on pressure distributions over wing having NA CA low drag profile; for lift coefficients ranging from 0 to 0.60, no appreciable compressibility effects on spanwise wing loading were noted below 0.75 Mach number; above this Mach number inboard lateral shift of load occurred.
Wing pressure-distribution measurements up to 0,866 Mach number in flight on jet-propelled airplane
Nat Advisory Committee Aeronautics -- Tech Note
1947
17 pages
Supp Plates
Report
Englisch
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Engineering Index Backfile | 1946
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