Transonic Inlet Flow Calculations Using a General Grid-Generation Scheme

[+] Author and Article Information
L. T. Chen, D. A. Caughey

McDonnell Douglas Research Laboratories, McDonnell Douglas Corporation, St. Louis, Mo. 63166

J. Fluids Eng 102(3), 309-315 (Sep 01, 1980) (7 pages) doi:10.1115/1.3240687 History: Received April 01, 1979; Online October 26, 2009


Finite difference solutions for transonic flowfields about engine inlet nacelles are obtained by combining a general grid-generation scheme with a previously developed general solver for transonic potential flowfields (1). The grid-generation scheme is similar to Thompson’s method, but uses simpler equations to solve for the mesh coordinates. An extrapolated relaxation procedure is used to obtain improved convergence of the transonic solution to small residuals. Results obtained for flowfields with embedded supersonic regions both outside and inside the inlets compare well with experimental results.

Copyright © 1980 by ASME
Your Session has timed out. Please sign back in to continue.






Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In