Hypersonic Viscous Interaction on Slender Cones
Author | : C. C. Horstman |
Publisher | : |
Total Pages | : 12 |
Release | : 1968 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
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Author | : C. C. Horstman |
Publisher | : |
Total Pages | : 12 |
Release | : 1968 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Author | : G. M. Gregorek |
Publisher | : |
Total Pages | : 64 |
Release | : 1959 |
Genre | : Ultrasonic waves |
ISBN | : |
Author | : V. S. Nikolaev |
Publisher | : |
Total Pages | : 20 |
Release | : 1967 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Author | : Marvin I. Kussoy |
Publisher | : |
Total Pages | : 20 |
Release | : 1967 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Harold Mirels |
Publisher | : |
Total Pages | : 76 |
Release | : 1967 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Effects of viscous interaction are investigated for hypersonic flow over slender axisymmetric bodies. The entire range of interaction, from weak to strong, is considered for nose bluntness not greater than a 3/4 power law. Extensive numerical results are given for the self-similar flow over a 3/4 power law body. These results are correlated and used in a local similarity procedure for finding viscous interaction over arbitrary body shapes. Analytical expressions are derived for weak interaction on a cone and strong interaction on power law bodies. Following Dewey's approach, the local similarity procedure is simplified to a series of algebraic equations. These are solved for flow of air over a cone. Numerical results are presented for cone surface pressure, shear, heat transfer, drag and displacement thickness in all interaction regimes. The drag is in good average agreement with available experimental cone drag data. The analytical development is a unified treatment of viscous interaction effects on two-dimensional as well as axisymmetric bodies. Numerical results for wedges are included. (Author).
Author | : W. Carson Lyons (Jr.) |
Publisher | : |
Total Pages | : 72 |
Release | : 1968 |
Genre | : Cone |
ISBN | : |
A computer program is presented for calculating the various components comprising the total drag coefficient for slightly blunted slender cones. The program is applicable for either the case of a completely laminar boundary layer or where transition occurs on the cone. Weak viscous interaction effects are taken into account. Local flow properties which exist at the outer edge of the boundary layer along the cone are also computed. (Author).
Author | : Lawrence Talbot |
Publisher | : |
Total Pages | : 34 |
Release | : 1958 |
Genre | : Cones |
ISBN | : |
Viscous self-induced pressures on 3 degree-semivertex-angle cones were measured over the range 3.7
Author | : H. F. Waldron |
Publisher | : |
Total Pages | : 0 |
Release | : 1966 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
An experimental and analytical study of viscous hypersonic flow over pointed cones with particular emphasis on the viscous-layer regime is presented. Shock tunnel measurements of heat transfer to 5, 10 and 20 degree half-angle cones and of pressure on the 20 degree cone are compared with the predictions of a viscous-inviscid interaction analysis (Probstein and Elliot) including transverse curvature, of a viscous-layer nonslender cone analysis (Cheng) and of an extension of the nonslender cone analysis incorporating effects of slenderness. The large rise in heat transfer predicted by the transverse curvature theory is not observed and close agreement is obtained with the nonslender cone viscous-layer predictions. An extension of the nonslender cone analysis is presented where the effects of cone slenderness are included by a perturbation analysis. The solution of the resulting equations reveals that the net effect of transverse curvature and of other effects associated with cone slenderness is small in the viscous-layer regime for not-too-slender cones. Good agreement of the 10 and the 20 degree cone experimental data is obtained with this extension of the nonslender solution. (Author).
Author | : Kazimierz J. Orlik-Rueckemann |
Publisher | : |
Total Pages | : 3 |
Release | : 1971 |
Genre | : |
ISBN | : |
Unsteady pressure distributions and stability derivatives on a slender circular cone performing oscillation in pitch in viscous hypersonic flow can be determined using the method of dynamic viscous pressure interaction developed by the present author. The method takes into account the relative motion between the body surface and the boundary-layer displacement surface and can be applied to arbitrary bodies and flow conditions, provided the relevant inviscid unsteady pressure distributions and the dependence of the boundary-layer displacement on the steady flow variables are known. In the present paper, practical closed-form formulas are given for the unsteady pressure distribution and the static and dynamic pitching moment derivatives for a slender right circular cone performing low-frequency, small-amplitude oscillation in pitch around zero mean incidence and completely submerged in the weak-interaction region of laminar boundary layer. (Author).
Author | : Harold Mirels |
Publisher | : |
Total Pages | : 30 |
Release | : 1969 |
Genre | : |
ISBN | : |
Hypersonic viscous flow about slender cones, wedges, and 3/4 power law bodies is considered. Body thickness ratios leading to minimum drag are determined subject to constraints of fixed base, fixed volume, or fixed surface area. It is assumed that the shocks are strong and that the fluid is ideal. It is found that minimum drag occurs in a flow region where viscous interaction and, for axisymmetric bodies, transverse curvature must be taken into account. Numerical results are given for optimum thickness ratio and minimum drag as a function of altitude. (Author).