Vortical Flows on the Lee Surface of Delta Wings

  • K. Y. Narayan
  • S. N. Seshadri
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)


In the more than three decades of research on the lee surface flow of delta wings, starting from the identification of a single pair of counter-rotating vortices springing from the leading edges, multiple vortices (secondary, tertiary), “squashed” vortices, vortices embedded in boundary layers, shock waves on the wing, on, underneath and in between the vortices, shock wave boundary layer interaction, shock-induced separation, vortex bursting, asymmetric flow behaviour and so on have been progressively “discovered”. In a gross sense, the geometric and free stream conditions under which each of these flow phenomena occurs are reasonably well understood. However, the physical mechanisms underlying some of the flow phenomena remain far from clear. Significant progress has been made in recent times in the computation of the complex three-dimensional flows on delta wings; however, solutions for even the simplest flow type (flow with a pair of leading edge vortices) tax the resources of the largest available computer. Solutions for the more complex flow types including multiple separations, shocks, etc., appear to be realisable only in the distant future.


Shock Wave Mach Number Primary Vortex Delta Wing Lead Edge Vortex 
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  1. 1.
    Szodruch, J.: Leeseiten-Strömung bei schlanken Delta Flügeln endlicher Dicke. ILR-BERICHT 23, Technische Universität Berlin, 1977.Google Scholar
  2. 2.
    Miller, D.S., Wood, M.W.: Lee-Side Flow Over Delta Wings at Supersonic Speeds. NASA TP-2430, 1985.Google Scholar
  3. 3.
    Seshadri, S.N., Narayan, K.Y.: Lee-Surface Flow Over Delta Wings at Supersonic Speeds. NAL TM AE 8610. 1986.Google Scholar
  4. 4.
    Elsenaar, A (Ed).: Proceedings of a Symposium on International Vortex Flow Experiment on Euler Code Validation. Stockholm 1986.Google Scholar
  5. 5.
    Narayan, K.Y., Hartmann, K.: Transonic and Supersonic Flow Past a 65 Degree Delta Wing with Rounded Leading Edges - Analysis of Experimental Data - To be published as DFVLR FB.Google Scholar
  6. 6.
    Seshadri, S.N., Narayan, K.Y.: Shock-Induced Separated Flows on the Lee Surface of Delta Wings. Aero.Jour., Vol.91, No.903 (1987), 128–141.Google Scholar
  7. 7.
    Michael, W.H.: Flow Studies on Flat-Plate Delta Wings at supersonic Speeds. NACA TN 3472, 1955.Google Scholar
  8. 8.
    Vorropoulos, G., Wendt, J.F.: Laser Velocimeter Study of Compressibility Effects on the Flow Field of Delta Wings. AGARD CP-342, 1983.Google Scholar
  9. 9.
    Rizzi, A.: Euler Solutions of Transonic Vortex Flow Around the Dillner Wing. J.Aircraft, Vol.22, No.4 (1985), 325–328.CrossRefGoogle Scholar
  10. 10.
    Szodruch, J., Ganzer, U.: On the Lee-Side Flow Over Delta Wings at High Angle of Attack. AGARD CP-247, 1978.Google Scholar
  11. 11.
    Sutton, E.P.: Some observations of the Flow Over a Delta-Winged Model with 55 Degree Leading-Edge Sweep, at Mach Numbers between 0.4 and 1.8. ARC R&M No. 3190, 1960.Google Scholar
  12. 12.
    Hall, I.M., Rogers, E.W.E.: The Flow Pattern on a Tapered Swept-Back Wing at Mach Numbers between 0.6 and 1.8. ARC R&M No.3271, 1957.Google Scholar
  13. 13.
    Kulfan, R.M.: Wing Airfoil Shape Effects on the Development of Leading-Edge Vortices. AIAA Paper No.79–1675, AIAA Atmospheric Flight Mechanics Conference, 1979.Google Scholar
  14. 14.
    Manro, G.N., Manning, K, Hallstaff, T.H., Rogers, J.T.: Transonic Pressure Measurements and Comparison of Theory to Experiment for an Arrow Wing Configuration. NASA CR-2610, 1976.Google Scholar
  15. 15.
    Boersen, S.J., Elsenaar, A.: Tests on the AFWAL 65 Degree Delta Wing at NLR:A Study of Vortex Flow Development between Mach=0.4 and 4. Proc. Symp. on Intl. Vortex Expt. on Euler Code Validation, Stockholm, 1986.Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1989

Authors and Affiliations

  • K. Y. Narayan
    • 1
  • S. N. Seshadri
    • 1
  1. 1.Aerodynamics DivisionNational Aeronautical LaboratoryBangaloreIndia

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