Analog Study of Supersonic Conical Flows

The governing equation of the perturbation potential for linearized three-dimensional supersonic flow is given by

Подпись:2 д2ф д2ф д2у

дх2 ду2 dz2

where в2 = M2 – 1.

When the flow is conical, p depends only on two variables as follows. Let

Подпись: (13.70)у = r cos в, z = r sin в, x = firX

then, any of the three velocity components, u, v, w depend only on в and X. For X = cos £, a Laplace equation is obtained for the flow interior to the mach cone

(13.71)

For X > 1 (exterior of the mach cone), with X = cosh £, the wave equation is obtained

For more details, see Stewart [13].

Analog Study of Supersonic Conical Flows Analog Study of Supersonic Conical Flows
Подпись: i в

To study the flow inside the Mach cone, the complex variable Z = gel6, where

Either u, v,w may be identified with the electrical potential in a plane circular tank.

Germain [14] analyzed in detail the analog representation for a flat plate inside the Mach cone. he also studied wings with different cross sections and with dihedral angles. The study of wings in supersonic flow regime, steady and unsteady, was carried out by Enselme [15].

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