Journal of Thermal Science

, Volume 15, Issue 1, pp 31–36 | Cite as

Flow visualization around a double wedge airfoil model with focusing schlieren system

  • Masashi Kashitani
  • Yutaka Yamaguchi
Article
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Abstract

In the present study, aerodynamic characteristics of the double wedge airfoil model were investigated in a transonic flow by using the shock tube as an intermittent wind tunnel. The driver and driven gases of the shock tube are dry air. The airfoil model of double wedge has the span of 58 mm, chord length c = 75 mm and its maximum thickness is 7.5 mm. The apex of the double wedge airfoil model is located on the 35% chord length from the leading edge. The range of hot gas Mach numbers are from 0.80 to 0.88, and the Reynolds numbers based on chord length are 3.11 × 105 ∼ 3.49 × 105, respectively. The flow visualizations were performed by the sharp focusing schlieren method which can visualize the three dimensional flow fields. The results show that the present system can visualize the transonic flowfield clearer than the previous system, and the shock wave profiles of the center of span in the test section are visualized

Keywords

shock wave schlieren method transonic flow double wedge airfoil model 

CLC number

V211.7 
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References

  1. [1]
    Shapiro, A H. The Dynamics and Thermodynamics of Compressible Fluid Flow. New York: The Ronald Press Company, 1980, 445–447Google Scholar
  2. [2]
    Puckett, A E, Stewart, H J. Aerodynamics Performance of Delta Wing at Supersonic Speeds. J. Aeronautical Sciences, 1947, 17, 567–578MathSciNetGoogle Scholar
  3. [3]
    Weinstein, L M. An Improved Large-Field Focusing Schlieren System. AIAA 91-0567, 1991Google Scholar
  4. [4]
    Gartenberg, E, Weinstein, L M, Lee, Jr., E. E. Aerodynamic Investigation with Focusing Schlieren in Cryogenic Wind Tunnel. AIAA J., 1994, 32(6): 1242–1249ADSCrossRefGoogle Scholar
  5. [5]
    Cook, S P, Chokani, N. Quantitative Results from the Focusing Schlieren Technique. AIAA 93-0630, 1993Google Scholar
  6. [6]
    Kashitani, M, Yamaguchi, Y, Saito, T. Observation of Shock Tube Airfoil Flow with a Sharp Focusing Schlieren Method. Theoretical and Applied Mechanics, 2000, 49: 249–255Google Scholar
  7. [7]
    Cook, W J, Presley, L L, Chapman, G T. Shock Tube as a Device for Testing Transonic Airfoils at High Reynolds Numbers. AIAA J., 1979, 17(7): 714–721ADSGoogle Scholar
  8. [8]
    Kashitani, M, Yamaguchi, Y, Nakao, S. Visualization of a Double Wedge Airfoil Model in a Transonic Shock Tube Flow. NCTAM2003, 2003. 307–308Google Scholar

Copyright information

© Science Press 2006

Authors and Affiliations

  • Masashi Kashitani
    • 1
  • Yutaka Yamaguchi
    • 1
  1. 1.Department of Aerospace EngineeringNational Defense AcademyKanagawaJapan

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