An application of the compressibility correction developed by Lieblein and Stockman (1972) to the calculation of flow in axisymmetric inlets is described. The results with experimental data from wind tunnel model tests are compared. The configuration is a conventional subsonic inlet with a NACA series one external cowl shape and a two-to-one ellipse internal lip. It is shown that the compressibility correction gives a relatively good approximation to the internal compressible flow behavior, and thus should be useful in the design and analysis of engine nacelle inlets.
Application of compressibility correction to calculation of flow in inlets.
Application of compressibility correction to calculation of flow in inlets ; 1973
1973-07-01
Conference paper
No indication
English
Calculation of Transonic Flow around Axisymmetric Inlets
AIAA | 1975
|Calculation of transonic flow around axisymmetric inlets
AIAA | 1975
|Compressibility Correction for Internal Flow Solutions
AIAA | 1972
|Compressibility correction for flow about wing surfaces
AIAA | 1984
|