Systematic method for computer design of supercritical airfoils in cascade
Journal Article
·
· Commun. Pure Appl. Math.; (United States)
A computer code has been developed for the direct calculation of shockless transonic airfoils whose pressure distributions can be assigned within reasonable limits. The code is fast and accurate, so that a range of numerical examples can be produced at will. Experience with analysis programs and wind tunnel tests suggests that shockless airfoils designed this way provide a valid first stage in the development of supercritical wing sections. It would be desirable, however, to conduct a more detailed investigation of the effectiveness of the method in suppressing boundary layer separation and drag creep.
- OSTI ID:
- 7308741
- Journal Information:
- Commun. Pure Appl. Math.; (United States), Journal Name: Commun. Pure Appl. Math.; (United States) Vol. 29; ISSN CPAMA
- Country of Publication:
- United States
- Language:
- English
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