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Comparison of wind-tunnel test results at M(infinity) = 0.7 with results from the boeing tea-230 subsonic flow method

Comparison of wind-tunnel test results at M(infinity) = 0.7 with results from the boeing tea-230 subsonic flow method - - Washington, D.C. National Aeronartics and Space Administration 1975 - 91 p. - NASA CR 2554 : 1975 .

ISBN:

Subjects--Topical Terms:

Potential flow analysis, Wind tunnel data, Pressure distribution, Test-theory comparison, Overwing nacelle

Universal Decimal Class. No.: LNASA CR 2554 : 1975

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