Hypersonic Flutter Model Tests of Advanced Wing Configurations at Initial Angles of Attack.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1964
- Accession Number
- AD0355284
Entities
People
- S. R. Hurley