Accession Number:

AD0355755

Title:

FLUTTER MODEL TESTS OF ADVANCED WING CONFIGURATIONS AT INITIAL ANGLES OF ATTACK

Descriptive Note:

Corporate Author:

NORTH AMERICAN AVIATION INC COLUMBUS OH

Personal Author(s):

Report Date:

1964-10-01

Pagination or Media Count:

127.0

Abstract:

This report describes an experimental and analytical program conducted to determine the transonic and supersonic flutter boundary of a highly swept, low aspect ratio lifting surface typical of re-entry vehicle configurations. Several semi-rigid flutter models were constructed and tested at Mach numbers from .4 to 1.2 and also at Mach numbers from 2.0 to 5.0. The effects on flutter speed of initial angle of attack, un-coupled frequency ratio, model thickness ratio and a tip surface normal to the plane of the basic model were determined. The model aspect ratio was .889, the leading edge sweep angle was 70 degrees and the thickness ratio of the basic model was 6. Other thicknesses were 3 and 9. The cross-section of the model was modified wedge having a wedge angle in the streamwise direction of 22 degrees 38 minutes. The trailing edge was blunt. Author

Subject Categories:

  • Aerodynamics
  • Unmanned Spacecraft
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE