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Singularities of the Flow Field in the Neighborhood of the Windward Surface of a Small Aspect Ratio Delta Wing in Hypersonic Stream

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Abstract—

Significantly inhomogeneous gas flow in the neighborhood of the lower surface of a plain delta wing at an angle of attack in hypersonic stream is considered. The most general case of narrow wing with the bow shock attached to the leading edge or detached from it is studied in the analytical solution of the problem obtained with the use of the asymptotic thin shock layer method. In the solution with the attached shock wave, “singular cross-sections” which are normal to the wing and have breaks of the stream surfaces due to the action of concentrated forces are found. Their input to the aerodynamic characteristics is evaluated. In flow with the detached shock, the distinctive feature of the solution relates to the formation of a thin entropy layer on the wing surface. In this layer the flow is formed under the action of the side pressure gradient. Examples of universal solutions valid for the flow description through the “external” main shock layer part and the “internal” entropy layer are constructed.

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  1. Zhukovsky Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia

    V. N. Golubkin

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  1. V. N. Golubkin
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Correspondence to V. N. Golubkin.

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Translated by E.A.Pushkar

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Golubkin, V.N. Singularities of the Flow Field in the Neighborhood of the Windward Surface of a Small Aspect Ratio Delta Wing in Hypersonic Stream. Fluid Dyn 56, 699–717 (2021). https://doi.org/10.1134/S0015462821050037

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