AN INVESTIGATION OF AERODYNAMIC CONTROLS AT HYPERSONIC MACH NUMBERS.
Abstract
A research program was conducted to investigate the behavior of a flat plate wing with a semi-cylindrical leading edge at a Mach number of 13.87 and a Reynolds number, based on the leading edge thickness, of 3935.0. The wing was investigated with both a trailing and leading edge control surface. Data were obtained at various combinations of angles of attack and control surface deflections. Pressure distributions for each control surface location, in the presence of combined separated and expansion type flow fields, were obtained. These pressure distributions were integrated and the resulting two-dimensional force and moment coefficients, lift-to-drag ratio, and location of the center of pressure were compared with inviscid theory. The results of the research are presented in three groups; the first series of tests were conducted at various angles of attack for the case where the control surface was not deflected. The second series of data indicate the effect of cross-flow through an open gap between the wing and the control surface on the local pressure distribution. Finally, the third group of data present the experimental data with theoretical correlation of such parameters as control effectiveness and aerodynamic hinge moments for both the trailing edge and leading edge control surface location at various angles of attack. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1967
- Accession Number
- AD0657285
Entities
People
- Anthony W. Fiore
Organizations
- Air Force Research Laboratory