Accession Number:

AD0851095

Title:

Aeroelastic Stability Tests of Thin Cylindrical Shells at Supersonic Speeds (Follow-On Tests)

Descriptive Note:

Final rept.

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1969-04-01

Pagination or Media Count:

24.0

Abstract:

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.

Subject Categories:

  • Guided Missiles
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE