Numerical simulation of subsonic air plasma flow about a cooled pitot tube

Porterie, B.; Loraud, J. C.; Larini, M.; Jestin, Louis

doi:10.2514/6.1992-4004

Cited by 3 publications

(2 citation statements)

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“…To our knowledge, these are the first reported simulations of this type for highspeed plasmas. Porterie et al (9) have reported previous simulations in a similar spirit for subsonic low-temperature flow past a cooled Pitot tube. Those simulations were performed assuming chemical equilibrium under conditions of negligible ionization, whereas the present situation requires a full nonequilibrium description, including finite-rate ionization kinetics.…”

Section: Vl = MI (7rg Ti) I/2 (3)mentioning

confidence: 76%

Computational study of high-speed plasma flow impinging on an enthalpy probe

Chang

Ramshaw

1996

Plasma Chem Plasma Process

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Section: Vl = MI (7rg Ti) I/2 (3)mentioning

confidence: 76%

Computational study of high-speed plasma flow impinging on an enthalpy probe

Chang

Ramshaw

1996

Plasma Chem Plasma Process

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“…This work completes and improves on that of a former article 33 where the governing equations were solved using the wellknown MacCormack's scheme for the subsonic case (0.3 < M.,_ < 0.8). Furthermore, it is based on a numerical method well suited to the calculation of the steady-state solution and which allows one to extend the domain of application to the low-subsonic case (up to M v _ = 0.1).…”

Section: Introductionmentioning

confidence: 81%

Cooled pitot tube in plasma jet - An impact-pressure recovery model

Porterie

Larini

Loraud

et al. 1994

Journal of Thermophysics and Heat Transfer

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The time-dependent axisymmetric Navier-Stokes equations are numerically integrated to predict the steadystate pressure at the forward critical point of a cooled pitot tube immersed in an air plasma flow. The flow is assumed to be in chemical equilibrium. Real gas chemistry is coupled to the gasdynamics by means of a Gibbs free energy minimization package. A Runge-Kutta multistage time integration to the central discretization of the flux balance is used. Local time stepping and residual averaging technique are used to accelerate the convergence to the steady state. Numerical results are presented for subsonic and transonic air plasma flows at four Mach numbers from 0.1 to 0.8 for gas temperature in the range of 300-5000 K. The computed values of the impact pressure are compared to values obtained from theoretical and semiempirical relations. The comparative examination indicates that the computed impact pressure is much more sensitive to the temperature difference between the gas and the pitot tube. It is found that this effect becomes greater for lower freestream Mach number which is consistent with the experimental results of Hare. Additional calculations also reveal that this effect increases as the freestream pressure decreases.

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Jankovic

Mostaghimi

1998

Plasma Chemistry and Plasma Processing

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Numerical simulation of subsonic air plasma flow about a cooled pitot tube

Cited by 3 publications

References 4 publications

Computational study of high-speed plasma flow impinging on an enthalpy probe

Computational study of high-speed plasma flow impinging on an enthalpy probe

Cooled pitot tube in plasma jet - An impact-pressure recovery model

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