Modal Instabilities over Blunted Cones at Angle of Attack in Hypersonic Flow

What is it about?

The effects of nose radius and angle of attack on the linear modal amplification over blunt circular cones at Mach 10 are computationally investigated. Results indicate that the linear amplification of stationary and traveling crossflow waves along inflection lines, as well as of Mack's second mode waves along streamlines, increases with the angle of attack and decreases with the nosetip radius.

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