Results of measurements made during high speed wind tunnel tests presented for angles of attack ranging from 0.2 to 21.2° and for free stream Mach numbers ranging from 0.2 to about 0.7.
Effect of compressibility on distribution of pressures over tapered wing of NACA 230-series airfoil sections
Nat Advisory Committee Aeronautics -- Tech Note
1947
11 pages
24 Supp Sheets
Report
English
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Engineering Index Backfile | 1948
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