Determining aerodynamic coefficients from high speed video of a free-flying model in a shock tunnel

Andrew J. Neely; Ivan West; Robert Hruschka; Gisu Park; Neil R. Mudford

doi:10.1117/12.823081

10 February 2009 Determining aerodynamic coefficients from high speed video of a free-flying model in a shock tunnel

Andrew J. Neely, Ivan West, Robert Hruschka, Gisu Park, Neil R. Mudford

Proceedings Volume 7126, 28th International Congress on High-Speed Imaging and Photonics; 71260H (2009) https://doi.org/10.1117/12.823081
Event: 28th International Congress on High-Speed Imaging and Photonics, 2008, Canberra, Australia

Abstract

This paper describes the application of the free flight technique to determine the aerodynamic coefficients of a model for the flow conditions produced in a shock tunnel. Sting-based force measurement techniques either lack the required temporal response or are restricted to large complex models. Additionally the free flight technique removes the flow interference produced by the sting that is present for these other techniques. Shock tunnel test flows present two major challenges to the practical implementation of the free flight technique. These are the millisecond-order duration of the test flows and the spatial and temporal nonuniformity of these flows. These challenges are overcome by the combination of an ultra-high speed digital video camera to record the trajectory, with spatial and temporal mapping of the test flow conditions. Use of a lightweight model ensures sufficient motion during the test time. The technique is demonstrated using the simple case of drag measurement on a spherical model, free flown in a Mach 10 shock tunnel condition.

Citation Download Citation

Andrew J. Neely, Ivan West, Robert Hruschka, Gisu Park, and Neil R. Mudford "Determining aerodynamic coefficients from high speed video of a free-flying model in a shock tunnel", Proc. SPIE 7126, 28th International Congress on High-Speed Imaging and Photonics, 71260H (10 February 2009); https://doi.org/10.1117/12.823081

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