Subsonic dynamic stability experiment on the anti-tank missile model

Abstract

One of the most difficult aspects of aircraft and missile development is defining stability and control characteristics. The best way to obtain model-scale dynamic stability derivatives is to perform experiments in wind tunnels having high Reynolds number. In the T-38 wind tunnel the forced oscillation technique is used for the measurement of stability derivatives. This technique enables measurements of the full complement of damping, cross and cross-coupling moment derivative due rolling, pitching and yawing. Results of the experimental determination of the roll-damping derivative for the Anti Tank Missile Model are presented in this paper. The missile model was designed and produced by Military Technical Institute. The roll damping tests were conducted at Mach numbers 0.2, 0.4 and 0.6. The roll-apparatus, used in these tests, is apparatus with primary angular oscillation around a longitudinal axis of a model. Roll-damping coefficients, measured in the T-38 wind tunnel, are compared with results obtained by the semi-empirical method DMAC.

Keywords

• wind tunnel
• missile model
• stability derivative
• roll-damping derivative
• oscillations
• forced oscillation technique