By G. G. Chernyi
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Extra resources for Introduction to Hypersonic Flow
Are devoted to the study of the generalized solutions of this equation. The most complete treat ment of the problem, together with a bibliography of related papers, is contained in the work of Oleinik , which may be consulted by the interested reader. 3. Characteristic properties of hypersonic flows The kinetic energy of the gas particles in a hypersonic flow is large compared to their thermal energy. For fixed values of the state param eters, the ratio of the kinetic to the internal energy in the free stream increases in proportion to the square of the Mach number M.
Drag coefficients for a sphere and a cone-cylinder: 0-, 3-, #-. the drag coefficients remain practically unchanged for free stream Mach numbers greater than 3 or 4. In addition, the flow pattern in the neigh borhood of the body remains unchanged. As an example, experimental values of the drag coeflScients for a sphere and a cone-cylinder obtained from ballistic tests are shown in Fig. 8 [15-17]. 50 GENERAL CONSIDERATIONS FOR IDEAL GAS FLOWS [CHAP. I The proof of the existence of a Umiting state of flow near a body for Μ —> 00 was given by S.
The axis Ox is taken in the direction of the free stream flow, and the axes Oy and Oz orthogonal to each other in a plane normal to this direction (Fig. 2). FIG. 2. Coordinate system. According to the assumption made previously about the shape of the body, the angle between the normal to the surface η and the direction of the free stream at points on the forward portion of the body is close to 90 deg, so that cos (n, x) ' T. Here r is a small parameter—the thickness ratio of the body, or the maximum value of the angle between the surface of the forward portion of the body and the free stream direction, or the maximum value of cos (n, x), for example.
Introduction to Hypersonic Flow by G. G. Chernyi