Abstract
The effect of angles of attack in the interval 0 ≦α ≦40° on the flow pattern and the aerodynamic characteristics of a body of power-law shape (equation of the generator in the cylindrical coordinate system r=zn, n=0.125) is investigated for supersonic flow without injection and with intense subsonic localized injection from the surface. As a result of numerical calculations it is established that the use of Newton's theory for determining the coordinates of the gas stagnation point behind the shock in flow past an impermeable body of the shape in question leads to serious errors, and an expression for determining the location of this point is given. It is shown that for three-dimensional flow the flow pattern and the surface pressure distribution are sharply different from the caseα=0. It is established that on the parameter interval in question intense injection considerably reduces the aerodynamic drag without loss of static stability, which is important in connection with the solution of the problem of gas-stable aircraft control.
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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 95–101, September–October, 1987.
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Antonov, V.A., Grishin, A.M. & Pakhomov, F.M. Effect of angle of attack on supersonic flow past axisymmetric blunt bodies with surface injection. Fluid Dyn 22, 737–742 (1987). https://doi.org/10.1007/BF01051695
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DOI: https://doi.org/10.1007/BF01051695