AN EXPERIMENTAL SIMULATION OF GUST LOADING OF SUPERSONIC VEHICLES.
Abstract
A gust generator was installed in a supersonic wind tunnel, and gust-induced normal force and pitching moment were measured on a delta wing model. The generator simulates a periodic gust by directing high-pressure auxiliary air alternately upward and downward upstream of the supersonic test section. By this means angles of attack up to about 2 degrees (corresponding to gust velocities of about 70 feet per second) were induced in the Mach number 3 test section at nearly 100 cycles per second. The gust amplitude drops to about 1.2 degrees (40-50 feet per second) at 300 cycles per second and to approximately 0.2 degrees (7-10 feet per second) at 500 cycles per second. In this wind tunnel, a 500 cycle per second gust corresponds to a reduced frequency of about 1.2, based on wing semi-chord. The response of a delta wing to this periodic gust is measured by a strain gage balance. The balance and data-reduction equipment were designed to measure the phase and amplitude of the sinusoidal normal force and pitching moment at the fundamental gust frequency. The experiment demonstrates the feasibility of this type of supersonic gust simulation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1967
- Accession Number
- AD0825196
Entities
People
- Christopher J. Borland
- Leon H. Schindel
- Norbert A. Durando
- William G. Bousman
Organizations
- Massachusetts Institute of Technology