Results of measurements made in Langley two-dimensional low turbulence pressure tunnel at low Mach numbers and high Reynolds numbers; tests carried out for flap deflections of 0°, 4°, 7°, and 10°.
Pressure distributions and force tests of NACA 65-120 airfoil section with 50-percent-chord flap
Nat Advisory Committee Aeronautics -- Tech Note
1947
7 pages
61 Supp Plates
Report
Englisch
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Engineering Index Backfile | 1947
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