Wind tunnel boundary corrections using the wall signature method for a bluff body

Robert Ranzenbach, Chris Mairs, William Lasher

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Basic wind tunnel boundary correction schemes for closed jet test section wind tunnels are not generally applicable for complex flows about bluff bodies whose frontal area exceeds approximately 7.5% of the cross-sectional area of the test section. When model sizes are greater than 7.5%, advanced boundary correction schemes capable of resolving wind tunnel boundary effects are required. To evaluate the utility of an advanced boundary correction scheme, the Wall Signature Method was employed to study the drag produced by two dimensional flat plates of various sizes from 2.5% to 33% in a closed test section wind tunnel. Experimental and computational results of drag coefficient, uncorrected for blockage, as a function of blockage ratio already exist for this model problem. Additional results from a viscous computation, including tunnel wall pressures and flow streamlines, are included. Corrections were made to the drag coefficients using blockage correction factors determined using the Wall Signature Method. The blockage corrected drag coefficients were compared to the accepted freestream value. The validity of the supposition that pressure correction schemes work acceptably well for problems where the wake bubble may be distorted but the separation point remains fixed is studied.

Original languageEnglish (US)
Title of host publication17th Applied Aerodynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages497-501
Number of pages5
ISBN (Print)9781563472985
StatePublished - Jan 1 1999
Event17th Applied Aerodynamics Conference, 1999 - Norfolk, United States
Duration: Jun 28 1999Jul 1 1999

Publication series

Name17th Applied Aerodynamics Conference

Other

Other17th Applied Aerodynamics Conference, 1999
CountryUnited States
CityNorfolk
Period6/28/997/1/99

Fingerprint

Wind tunnels
Drag coefficient
Drag
Tunnels

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Ranzenbach, R., Mairs, C., & Lasher, W. (1999). Wind tunnel boundary corrections using the wall signature method for a bluff body. In 17th Applied Aerodynamics Conference (pp. 497-501). [AMA-99-31 64-CP] (17th Applied Aerodynamics Conference). American Institute of Aeronautics and Astronautics Inc, AIAA.
Ranzenbach, Robert ; Mairs, Chris ; Lasher, William. / Wind tunnel boundary corrections using the wall signature method for a bluff body. 17th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 1999. pp. 497-501 (17th Applied Aerodynamics Conference).
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Ranzenbach, R, Mairs, C & Lasher, W 1999, Wind tunnel boundary corrections using the wall signature method for a bluff body. in 17th Applied Aerodynamics Conference., AMA-99-31 64-CP, 17th Applied Aerodynamics Conference, American Institute of Aeronautics and Astronautics Inc, AIAA, pp. 497-501, 17th Applied Aerodynamics Conference, 1999, Norfolk, United States, 6/28/99.

Wind tunnel boundary corrections using the wall signature method for a bluff body. / Ranzenbach, Robert; Mairs, Chris; Lasher, William.

17th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 1999. p. 497-501 AMA-99-31 64-CP (17th Applied Aerodynamics Conference).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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Ranzenbach R, Mairs C, Lasher W. Wind tunnel boundary corrections using the wall signature method for a bluff body. In 17th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA. 1999. p. 497-501. AMA-99-31 64-CP. (17th Applied Aerodynamics Conference).