Aeroelastic Stability Tests of Thin Cylindrical Shells at Supersonic Speeds (Follow-On Tests)
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Follow-on tests to an investigation to determine the dynamic characteristics of thin cylindrical shells were conducted. The model consisted of an ogive cylinder with the test shell located on the cylindrical portion of the model approximately 78 percent of the model length aft of the nose. Data were recorded at Mach numbers of 2.2 and 2.5 for 0-deg angle of attack and yaw. Flutter was induced on the 0.0020- and 0.0032-in.-thick shells by reducing the model cavity pressure. Boundary-layer measurements were also made at various boundary-layer blowing rates.
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