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Shock interference studies on a circular cylinder at Mach 16This paper presents the results of a computational study on the shock interference problems on a cylindrical body typical of an engine inlet cowl leading edge at a nominal Mach number of 16. The two-dimensional Navier-Stokes equations are solved assuming the flow to be in chemical and thermal equilibrium and using a finite element method. The algorithm employs a cell-centered fully implicit upwind scheme. Adaptively generated unstructured meshes of triangles and quadrilaterals are employed. Under certain conditions the finite element code resulted in oscillatory solutions for shock interference at Mach 16. Some of the causes of the unsteady behavior are identified, and to the extent possible, such situations are avoided in the present application. Two shock interference conditions involving a Type IV (supersonic jet) and a Type III (attaching shear layer) are solved. The results are compared with available experimental data and reasonable agreement is observed. A semi-empirical method is also used to estimate the maximum surface heat flux and static pressure.
Document ID
19900035179
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Prabhu, Ramadas K.
(Planning Research Corp. Hampton, VA, United States)
Thareja, Rajiv R.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Stewart, James R.
(Planning Research Corp. Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-0606
Accession Number
90A22234
Funding Number(s)
CONTRACT_GRANT: NAS1-18000
CONTRACT_GRANT: NAS1-19000
Distribution Limits
Public
Copyright
Other

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