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Approximate solution for unyawed circular cones at hypersonic speeds

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Summary

The effects of dissociation or ionization of air on inviscid hypersonic flow past a circular cone at zero angle of incidence, with an attached shock wave, are studied on the assumption of thermal equilibrium. An approximate closed form solution for the flow between the surface of the cone and the shock wave is obtained. Viscosity and heat conduction, etc., are completely neglected.

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Abbreviations

p :

pressure

ρ :

density

T:

absolute temperature

R, θ :

polar coordinates

u, v :

velocity components

a 2 :

(∂p/∂ρ) s , velocity of sound

α :

semivertical angle of the cone

ψ :

shock-wave angle

h :

specific enthalpy

q :

free-stream velocity

M:

free-stream Mach number

A, B:

constants

q max. :

maximum velocity of air corresponding to zero pressure

ν 1 :

ratio of specific heats in the absence of dissociation or ionization

ν 2 :

ratio of specific heats in the presence of dissociation or ionization

m 1 :

molecular weight of air in the absence of dissociation or ionization

m 2 :

effective molecular weight of air in the presence of dissociation or ionization

u 0 :

value ofu on the surface of the cone

C p :

pressure coefficient

CD :

drag coefficient

δ :

angle of deflection of the stream on the shockwave

β, β 1 :

angle of deflection of the stream at any point (R, θ) between the shock and the surface of the cone

References

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Authors and Affiliations

  1. Science College, Patna University, Patna

    Girishwar Nath

Authors
  1. Girishwar Nath
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Nath, G. Approximate solution for unyawed circular cones at hypersonic speeds. Proc. Indian Acad. Sci. 59, 207–226 (1964). https://doi.org/10.1007/BF03046436

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  • DOI: https://doi.org/10.1007/BF03046436

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