Publication Date:
2017-10-02
Description:
The effects of angle of attack on supersonic mixed compression inlet performance at four different locations about a hypothetical forebody are given. A computational method to predict optimum inlet location, orientation, and centerbody control schedule for design and off-design performance is described. The effects of inlet location and a forward canard on the angle-of-attack performance of a normal shock inlet at transonic speeds were studied. Proper integration of inlet location and a forward canard can enhance the angle-of-attack performance of a normal shock inlet. Two lower lip treatments for improving the angle-of-attack performance of rectangular inlets at transonic speeds are discussed.
Keywords:
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AGARD High Angle of Attack Aerodyn.; 10 p
Format:
text
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