Free-flight dynamic stability measurements of 10° half-angle cones with laminar and "tripped" boundary layers at supersonic speeds are presented and effects of Mach number, center-of-gravity position, and angle-of-attack oscillatory amplitude on dynamic stability are also shown; free-flight results show that dynamic stability is not perceptibly affected by state of boundary layer but is affected by amplitude of oscillation; data are compared with M.Tobak's potential flow solution and solution using Newtonian impact theory at all angles of attack.
Effect of boundary-layer transition on dynamic stability
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 1 ; p 46-52
1966
7 pages
Article (Journal)
English
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