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

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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].

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Authors and Affiliations

  1. Novosibirsk

    E. M. Prokhorov

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  1. E. M. Prokhorov
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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 6, pp. 154–160, November–December, 1985.

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Prokhorov, E.M. Optimal lifting surfaces of complicated-geometry wings at supersonic flight velocities. Fluid Dyn 20, 964–969 (1985). https://doi.org/10.1007/BF01049944

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