Publikationsdatum:
2019-06-27
Beschreibung:
Description of a procedure for predicting the flowfields that develop when successive interactions between oblique shock waves and a turbulent boundary layer occur. Such interactions may occur, for example, in engine inlets for supersonic aircraft. A control volume analysis is used to predict changes in the flow field across the interactions. Two bleed flow models are considered. The predicted results are compared with measured results and are shown to be in good agreement when the bleed flow rate is low, or when there is no bleed. Shortcomings of the bleed flow models at higher bleed flow rates are discussed.
Schlagwort(e):
AERODYNAMICS
Materialart:
Journal of Aircraft; 11; Jan. 197
Format:
text
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