Computation of the Base Flow for Axisymmetric Nacelle Configurations 971466
A flow modeling method has been developed to analyze the flow in the annular base (rear-facing surface) of a circular engine nacelle flying at subsonic speed but with a supersonic exhaust jet. Real values of exhaust gas properties and temperature are included. Potential flows of the air and gas streams are computed for the flow past a separated wake. Then a viscous jet mixing is superimposed on this inviscid solution. Conservation of mass, momentum and energy is achieved by mutiple iterations. Despite the iterations, the wake flow field is computed with modest computer requirements.
Citation: Baik, D., Zumwalt, G., and Hoffmann, K., "Computation of the Base Flow for Axisymmetric Nacelle Configurations," SAE Technical Paper 971466, 1997, https://doi.org/10.4271/971466. Download Citation
Author(s):
D. S. Baik, G. W. Zumwalt, K. A. Hoffmann
Affiliated:
Wichita State Univ.
Pages: 12
Event:
General, Corporate & Regional Aviation Meeting & Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
SAE 1997 Transactions - Journal of Aerospace-V106-1
Related Topics:
Gases
Simulation and modeling
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