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Flow measurements around a long axisymmetric body with varying cross section

Soltani, M. R ; Sharif University of Technology | 2005

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  1. Type of Document: Article
  2. Publisher: 2005
  3. Abstract:
  4. Supersonic flow over tapered bodies of revolution is investigated using both experimental and numerical methods. The experimental study consisted of a series of wind tunnel tests on an ogive-cylinder body and included the surface static pressure and boundary layer profiles measurements, at various angles of attack. Further, the flow around the model was visualized using Schlieren technique. All tests were conducted in the trisonic wind tunnel of Qadr Research Center, Iran. Static surface pressure results show that the circumferential pressure at different nose sections vary significantly with angles of attack, in contrast to the circumferential pressure signatures along the cylindrical part of the body. Total pressure measurements in the boundary layer, vary significantly both radially and longitudinally (along the body length). To study the effects of cross section variations on the pressure distribution and boundary layer profiles, several belts with various leading edge angles were installed at different locations along the cylindrical portion of the model. These belts caused major variations on both the surface pressure distributions and boundary layer profiles (especially after the middle belt). In addition, using the multi-block grid the thin layer Navier-Stokes (TLNS) equations was solved around the above models. Patched method is used near the interfaces. The numerical scheme uses implicit Beam-Warming central differencing; while Baldwin-Lomax turbulence modeling was used to close the Reynolds averaged Navier-Stokes equation. Good agreement is achieved when the numerical results are compared with the corresponding experimental data. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved
  5. Keywords:
  6. Axisymmetric body ; Static pressure ; Surface pressure ; Trisonic winds ; Boundary layers ; Computer simulation ; Mathematical models ; Pressure distribution ; Supersonic flow ; Turbulence ; Wind tunnels ; Flow measurement
  7. Source: 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, 10 January 2005 through 13 January 2005 ; 2005 , Pages 7221-7233
  8. URL: https://arc.aiaa.org/doi/10.2514/6.2005-50