High-enthalpy and perfect-gas heating measurements on a blunt cone

Hollis, Brian R.; Perkins, John N.

doi:10.2514/3.26812

Cited by 15 publications

(5 citation statements)

References 5 publications

(4 reference statements)

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“…Mach 10 Langley wind tunnel [6]. Overall, very good agreement between the simulation and the experiment was achieved.…”

supporting

confidence: 54%

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Experimental and Numerical Investigation of Hypervelocity Carbon Dioxide Flow over Blunt Bodies

Sharma¹,

Swantek²,

Flaherty³

et al. 2010

Journal of Thermophysics and Heat Transfer

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This paper represents ongoing efforts to study high-enthalpy carbon dioxide flows in anticipation of the upcoming Mars Science Laboratory and future missions. The work is motivated by observed anomalies between experimental and numerical studies in hypervelocity impulse facilities. In this study, experiments are conducted in the hypervelocity expansion tube that, by virtue of its flow acceleration process, exhibits minimal freestream dissociation in comparison with reflected shock tunnels, simplifying comparison with simulations. Shock shapes of the laboratory aeroshell at angles of attack of 0, 11, and 16 deg and spherical geometries are in very good agreement with simulations incorporating detailed thermochemical modeling. Laboratory shock shapes at a 0 deg of attack are also in good agreement with data from the LENS X expansion tunnel facility, confirming results are facility-independent for the same type of flow acceleration. The shock standoff distance is sensitive to the thermochemical state and is used as an experimental measurable for comparison with simulations and two different theoretical models. For low-density small-scale experiments, it is seen that models based upon assumptions of large binary scaling values do not match the experimental and numerical results. In an effort to address surface chemistry issues arising in high-enthalpy groundtest experiments, spherical stagnation point and aeroshell heat transfer distributions are also compared with the simulation. Heat transfer distributions over the aeroshell at the three angles of attack are in reasonable agreement with simulations, and the data fall within the noncatalytic and supercatalytic solutions.

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“…Mach 10 Langley wind tunnel [6]. Overall, very good agreement between the simulation and the experiment was achieved.…”

supporting

confidence: 54%

“…Hollis and Perkins compared various sphere-cone model forebody and aftbody heat transfer values with computational simulations in the NASA Hypersonic Pulse facility expansion tube [6,7] and the 31 in. Mach 10 Langley wind tunnel [6].…”

mentioning

confidence: 99%

Experimental and Numerical Investigation of Hypervelocity Carbon Dioxide Flow over Blunt Bodies

Sharma¹,

Swantek²,

Flaherty³

et al. 2010

Journal of Thermophysics and Heat Transfer

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“…This demands the presence of a thermal protection system not only at the nose but also at other parts of the surface of the re-entry vehicle at angle of attack. • Corner heating increases with the angles of attack and at 12 • forms a considerable fraction (around 70%) of the maximum heat measured on the cone surface as reported previously (Reddy 1980;Stewart & Chen 1994;Hollis & Perkins 1996). • Except at 12 • angle of attack, the heat transfer measurements irrespective of angle of incidence correlate very well when expressed in terms of St r .…”

Section: Surface Convective Heat Transfer Measurements On a Blunt Conesupporting

confidence: 79%

Simultaneous measurement of aerodynamic and heat transfer data for large angle blunt cones in hypersonic shock tunnel

Sahoo

Saravanan

Jagadeesh

et al. 2006

Sadhana

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Aerodynamic forces and fore-body convective surface heat transfer rates over a 60 • apex-angle blunt cone have been simultaneously measured at a nominal Mach number of 5•75 in the hypersonic shock tunnel HST2. An aluminum model incorporating a three-component accelerometer-based balance system for measuring the aerodynamic forces and an array of platinum thin-film gauges deposited on thermally insulating backing material flush mounted on the model surface is used for convective surface heat transfer measurement in the investigations. The measured value of the drag coefficient varies by about ±6% from the theoretically estimated value based on the modified Newtonian theory, while the axi-symmetric Navier-Stokes computations overpredict the drag coefficient by about 9%. The normalized values of measured heat transfer rates at 0 • angle of attack are about 11% higher than the theoretically estimated values. The aerodynamic and the heat transfer data presented here are very valuable for the validation of CFD codes used for the numerical computation of flow fields around hypersonic vehicles. Keywords. Aerodynamic and heat transfer data; large angle blunt cone; hypersonic flow shock tunnel.

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“…Since laminar computations on non-optimized grids may, incorrectly, be in qualitative agreement with turbulent data, comparisons with these computations could lead to incorrect conclusions about the state of the wake. An unpublished preliminary comparison with computational results from a non-optimized grid was one of the reasons that the experimental data discussed in the present paper were originally thought to result from a laminar wake 4 . While other issues such as flow quality, rarefaction effects, and thermochemical models in the CFD codes must also be investigated, the grid structure should also be considered as one of the possible reasons for the disagreement seen in wake heating comparisons such as Refs.…”

Section: Comparison Of Experiments and Computationsmentioning

confidence: 97%

Transition effects on heating in the wake of a blunt body

Hollis

Perkins

1997

32nd Thermophysics Conference

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A series of aerodynamic heating tests was conducted on a 70-deg sphere-cone planetary entry vehicle model in a Mach 10 perfect-gas wind tunnel at freestream Reynolds numbers based on diameter of 8.23x10 4 to 3.15x10 5 . Surface heating distributions were determined from temperature time-histories measured on the model and on its support sting using thin-film resistance gages. The experimental heating data were compared to computations made using an axisymmetric/2D, laminar, perfect-gas Navier-Stokes solver. Agreement between computational and experimental heating distributions to within, or slightly greater than, the experimental uncertainty was obtained on the forebody and afterbody of the entry vehicle as well as on the sting upstream of the free-shear-layer reattachment point. However, the distributions began to diverge near the reattachment point, with the experimental heating becoming increasingly greater than the computed heating with distance downstream from the reattachment point. It was concluded that this divergence was due to transition of the wake free shear layer just upstream of the reattachment point on the sting. Nomenclature B C,Hheating bias error

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High-enthalpy and perfect-gas heating measurements on a blunt cone

Cited by 15 publications

References 5 publications

Experimental and Numerical Investigation of Hypervelocity Carbon Dioxide Flow over Blunt Bodies

Experimental and Numerical Investigation of Hypervelocity Carbon Dioxide Flow over Blunt Bodies

Simultaneous measurement of aerodynamic and heat transfer data for large angle blunt cones in hypersonic shock tunnel

Transition effects on heating in the wake of a blunt body

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