The design of shockless airfoils that are appropriate for experimental work on a supersonic transport with an oblique wing are examined. A series of computer codes for the design and analysis of airfoils and wings in two dimensional and three dimensional transonic flow are studied. The oblique wing 3-D code was the forerunner of the later swept wing code. Techniques to incorporate the effect of an engine or fuselage in the inverse design code while using a minimum of computer resources are developed.
Study of transonic flow over swept wings
1983-01-01
Report
Keine Angabe
Englisch
Study of Transonic Flow over Swept Wings
NTIS | 1983
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