Application of compressibility correction to calculation of flow in inlets.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.
Document ID
19730051593
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Albers, J. A. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 7, 2013
Publication Date
July 1, 1973
Subject Category
Aerodynamics
Meeting Information
Meeting: Application of compressibility correction to calculation of flow in inlets