Abstract
We consider the problem of steady flow of an inviscid, non-heat-conducting gas about a delta wing which is spherically blunted at the nose and cylindrlcally blunded on the leading edges, at an angle of attack.
Several experimental and theoretical studies have been devoted to the investigation of this problem, of which we note [1–4], In the following the three-dimensional method of characteristics using the scheme proposed in [5] is used to calculate the flow fields about such bodies for freestream Mach numbers M=6, 7, 8, and ∞, sweep angle χ=70°, and angles of attack α from 0 to 15°.
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References
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Magomedov, K.M., Kholodov, A.S. Supersonic three-dimensional flow around a delta wing with blunted leading edges. Fluid Dyn 2, 113–117 (1967). https://doi.org/10.1007/BF01019555
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DOI: https://doi.org/10.1007/BF01019555