Fluid Dynamics

, Volume 20, Issue 6, pp 964–969 | Cite as

Optimal lifting surfaces of complicated-geometry wings at supersonic flight velocities

  • E. M. Prokhorov
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Abstract

Infinitely thin wings weakly perturbing a supersonic flow of perfect gas are investigated. The flow problem is solved in a linear formulation [1]. The shape of the wing in plan and the Mach number M∞ of the oncoming flow are specified. The optimal wing surface is determined as a result of finding the function of the local angles of attack αM(x, z) which ensures a minimum of the drag coefficient cx when there are limitations in the form of equalities on the lift coefficient cy and the pitching moment mz. A separationless flow regime is realized on the optimal wing for the given number M∞, and its subsonic leading edge does not experience a load [2].

Keywords

Mach Number Drag Coefficient Supersonic Flow Leading Edge Lift Coefficient 
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Copyright information

© Plenum Publishing Corporation 1986

Authors and Affiliations

  • E. M. Prokhorov
    • 1
  1. 1.Novosibirsk

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