Scale-effect tests in turbulent tunnel of NACA 653- 418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap. (Advance Confidential Report L4122 Sept 1944)
Scale-effect tests in turbulent tunnel of NACA 653- 418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap
Nat Advisory Committee Aeronautics -- Wartime Report
1944
10 pages
9 Supp plates
Report
English
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Engineering Index Backfile | 1944
|Wind-tunnel investigation of NACA 23012 airfoil with 0.30-airfoil-chord double slotted flap
Engineering Index Backfile | 1943
|Engineering Index Backfile | 1945
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