Low Reynolds number airfoil design for subsonic compressible flow.

R. H. Liebeck

Journal Article

Low Reynolds number airfoil design for subsonic compressible flow.

Liebeck R

LOW REYNOLDS NUMBER AERODYNAMICS. PROC. CONF., NOTRE DAME, U.S.A., JUNE 5-7, 1989 }EDITED BY T.J. MUELLER]. (LECTURE NOTES IN (1989) (54 ), Berlin, Germany, Springer-Verlag, 1989) 314-330

DOI: 10.1007/978-3-642-84010-4_23

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Abstract

Reports a study of aerofoils designed to provide high lift in the Reynolds number range of 0.5 to 5 million at Mach 0.4. This Mach number produces significant compressibility effects when design lift coefficient greater than 1.5 are desired. Four example aerofoils were developed with various thickness ratios and degree of aft loading. The MIT ISES analysis code was used to predict performance, including drag rise characteristics. Agreement with experimental wind tunnel data was good. The designs are being developed for the high altitude long endurance class of planes. (from author's abstract)

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Liebeck, R. H. (1989). Low Reynolds number airfoil design for subsonic compressible flow. LOW REYNOLDS NUMBER AERODYNAMICS. PROC. CONF., NOTRE DAME, U.S.A., JUNE 5-7, 1989 }EDITED BY T.J. MUELLER]. (LECTURE NOTES IN, (54 ), Berlin, Germany, Springer-Verlag, 1989), 314–330. https://doi.org/10.1007/978-3-642-84010-4_23

Low Reynolds number airfoil design for subsonic compressible flow.

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