COMPUTATION OF FLOW FIELD ABOUT SLENDER AIRCRAFT AT SUBSONIC TRANSONIC AND SUPERSONIC SPEEDS BY SLENDER AIRCRAFT THEORY (CALCUL DU CHAMP D'ECOULEMENT AUTOUR D'UN AERONEF EFFILE...)

Authors
  1. Chan, Y.Y.
Corporate Authors
Institute for Aerospace Research, Ottawa ONT (CAN);Chief of Research and Development, Ottawa ONT (CAN) Director Research and Development Air
Abstract
A computational method is presented for the calculation of the transonic flow field about slender aircraft. The method is based on the transonic slender aircraft theory and is shown to work well for simple wing-body configurations, as demonstrated by comparison with experimental data. Within the limit of the conventional slender body theory, the method can be applied to subsonic and supersonic speed ranges as well.
Report Number
NAE-LTR-HA-78 — Laboratory Technical Report
Date of publication
15 Jan 1987
Number of Pages
47
DSTKIM No
88-00746
CANDIS No
53987
Format(s):
Microfiche filmed at DSIS;Originator's fiche received by DSIS;Hardcopy

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