Hypersonic shock-tunnel testing at an equilibrium interface condition of 4100 K

Minucci, M. A. S.; Nagamatsu, H. T.

doi:10.2514/3.414

Cited by 22 publications

(4 citation statements)

References 5 publications

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“…The experiment was carried out in the RPI 0.61-m Hypersonic Shock Tunnel and it is described in Ref. 5. The agreement between theory and experiment is quite encouraging.…”

Section: Computer Program Hstr1mentioning

confidence: 73%

“…6 is believed to be caused mainly by viscous and shock overtaking effects. 10 These effects were not taken into account by the relatively simple theoretical model 5 used in the analysis. For more information about the HSTR1 algorithm architecture, the reader is referred to Ref.…”

Section: Computer Program Hstr1mentioning

confidence: 98%

“…The capacity of the HSTR1 algorithm to predict reservoir pressures and temperatures has been verified experimentally as discussed in Ref. 5. This reference presents numerical and experimental results for the RPI 0.61-m-diam Hypersonic Shock Tunnel operating at an equilibrium interface condition of 4100 K. The shock tunnel conditions used to produce this equilibrium interface are indicated in Fig.…”

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confidence: 98%

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Combustion shock tunnel and interface compression to increase reservoir pressure and enthalpy

Minucci¹,

Nagamatsu

Myrabo

1994

Journal of Thermophysics and Heat Transfer

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This article discusses the production of hypervelocitv -hypersonic flows in a combustion shock tunnel operating in the equilibrium interface mode. In this mode of operation, the additional compression provided by the approaching interface is used to obtain higher pressures and temperatures, as opposed to the reflected method. A computer code was developed to model the operation of a shock tunnel in the equilibrium interface condition. In this article, all the calculations were made for the Rensselaer Polytechnic Institute (RPI) 1.22-m-diam Combustion Driver Hypersonic Shock Tunnel. The major drawback of the interface compression technique, which is the contamination of the driven gas by the driver gas, was overcome through the utilization of a small volume region separating the two gases. Numerical results indicate that the RPI facility will be able to generate reservoir temperatures of the order of 20,000 K and reservoir pressures of the order of 30,000 psi. These reservoir conditions can be used to produce test section Mach numbers of 35. A h M P T Nomenclature cross-sectional area specific enthalpy Mach number pressure absolute temperature Subscripts c = corrected for area change at diaphragm station s -incident shock conditions t -shock tube conditions 1 = driven tube initial conditions 4 = driver tube postcombustion conditions 5 = reflected conditions oo = freestream conditions Superscripts , = equilibrium interface conditions * = nozzle throat conditions

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“…The experiment was carried out in the RPI 0.61-m Hypersonic Shock Tunnel and it is described in Ref. 5. The agreement between theory and experiment is quite encouraging.…”

Section: Computer Program Hstr1mentioning

confidence: 73%

Section: Computer Program Hstr1mentioning

confidence: 98%

mentioning

confidence: 98%

See 1 more Smart Citation

Combustion shock tunnel and interface compression to increase reservoir pressure and enthalpy

Minucci¹,

Nagamatsu

Myrabo

1994

Journal of Thermophysics and Heat Transfer

Self Cite

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“…A computer routine provided the shock-tube reservoir parameters by assuming isentropic compression from reflectedshock to reservoir states [18] and by using equilibrium-air parameters from NASA-9 coefficients [19]. First, the routine calculates reflected state properties from measured primary shock speed and initial driven temperature and pressure.…”

Section: Methodsmentioning

confidence: 99%

Single image molecular tagging velocimetry

Matos

Barreta

Martins

et al. 2020

Meas. Sci. Technol.

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A single-image nitric-oxide molecular tagging velocimetry (NO-MTV) is reported and employed in a real air driven hypersonic shock tunnel and provided velocities of 3240 ± 170(5.2%) and 3030 ± 160(5.3%) m s − 1 , insignificantly different from previous results of 3037 ± 98(3.2%) obtained by an ordinary multi-image MTV technique. The proposed methodology relies on an one-dimensional analytical description of the spatial intensity profile registered by a single MTV image.

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