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Experimental Data for the BACT Wing

This page presents a set of steady experimental data pertaining to the Benchmark Active Controls Technology Wing for Mach numbers ranging from 0.30 to 0.85. The original experiment was performed at the NASA Langley Transonic Dynamics Tunnel (TDT). The steady pressure tests were performed in the TDT with air as the fluid medium and the wing at an angle of attack that was approximately zero.


Geometry

The geometry for this test was a rectangular wing with a NACA 0012 cross-section, 16 inch chord, and 32 inch wing span. Transition strips made up of No. 30 carborundum grit were applied to the model approximately one inch back from the leading edge (approximately 6% chord) on both the upper and lower surfaces. The model was outfitted with 80 pressure transducers. Forty of the transducers were located at the 60% span station, and the other forty were located at the 95% span station.


Data

We have surface pressure data for the BACT wing at various angles of attack for seven different Mach numbers. Use the following links to download a plain text data file with the relevant data for each Mach number.


References

1. Rivera, J.A., Dansberry, B.E., Durham, M.H., Bennett, R.M., and Silva, W.A., "Pressure Measurements on a Rectangular Wing with a NACA 0012 Airfoil During Conventional Flutter," NASA TM 104211, National Aeronautics and Space Administration, 1992.

2. Stephens, C.H., "CFD-Based Aeroservoelastic Predictions on a Benchmark Configuration Using the Transpiration Method," Masters Thesis, Department of Mechanical and Aerospace Engineering, Oklahoma State University, 1998.


CASE Lab URL: http://www.caselab.okstate.edu/research/experiment/bact.html
Revised: March 7, 2001 [TJC]
Webmaster: caselab@gmail.com
Oklahoma State University