Accession Number:

AD0355284

Title:

Hypersonic Flutter Model Tests of Advanced Wing Configurations at Initial Angles of Attack.

Descriptive Note:

Technical documentary rept.,

Corporate Author:

NORTH AMERICAN AVIATION INC COLUMBUS OH

Personal Author(s):

Report Date:

1964-10-01

Pagination or Media Count:

210.0

Abstract:

This report presents an experimental and analytical flutter investigation of a low aspect ratio lifting surface with a 70 degree leading edge sweep angle, and thickness ratios of 3, 6, and 9 in the hypersonic speed range from M 5.0 to M 8.0. The 6 thickness ratio models were tested at uncoupled frequency ratios of 0.60, 0.75, and 0.90. The models used were of the semirigid type with a double wedge leading edge to 15 chord with constant thickness from the 15 chord to a blunt trailing edge. All experimental flutter configurations were analyzed using an analog representation of a quasi-steady flutter solution. The aerodynamic representations investigated were experimentally obtained static aerodynamic force coefficients and aerodynamic force coefficients derived from steady-state, two-dimensional, shock-expansion techniques with sweep angle corrections. The relative effect on the flutter characteristics of inclusion of piston theory derived rate terms in the aerodynamics was investigated for configurations.

Subject Categories:

  • Guided Missiles
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE