Publication Date:
2019-06-27
Description:
Linear theory is used, without two dimensional or slender body assumptions, to predict flow field produced by aircraft wing, nose, inlet, and pylons. Aircraft shock wave locations are predicted, and their effect on flow field is included through transformation of aircraft geometry. Program was written in FORTRAN IV for CDC 6400 computer.
Keywords:
MECHANICS
Type:
LAR-11250
Format:
application/pdf
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