Fore-body and base heat flux measurements on a typical crew module in short duration impulse facilities

Srinivasan, Karthik; Desikan, S. L. N.; Saravanan, R.; Kumar, Abhishek; Maurya, Praveen Kumar

doi:10.1016/j.applthermaleng.2016.04.111

Cited by 16 publications

(11 citation statements)

References 35 publications

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“…The platinum thin film gauge was calibrated for the coefficient of the change of resistance with temperature, and it was found to be 0.0029 K −1 . The thermal product of the substrate, Macor was 1900 J/m 2 /K/s 1/2 …”

Section: Methodsmentioning

confidence: 99%

“…Certain extreme missions like planetary exploration re‐entry probes still require dedicated base heat shields as the heating rates are demanding . Though lower base heat loads are a boon, they brings with them large uncertainties . Nonequilibrium flows, chemical reactions, rarefied flows, transport property estimation errors, unsteadiness, transition, etc., existing in the wake flow field, make the prediction and modeling of such flows complex, mandating experimentation to review the numerical approach …”

Section: Introductionmentioning

confidence: 99%

“…5,6 Though lower base heat loads are a boon, they brings with them large uncertainties. 7 Nonequilibrium flows, chemical reactions, rarefied flows, transport property estimation errors, unsteadiness, transition, etc., existing in the wake flow field, make the prediction and modeling of such flows complex, mandating experimentation to review the numerical approach. 8 The heat flux distribution at the base of such a re-entry capsule is influenced by the near wake region, characterized by the corner expansion fan, free shear layer, recompression zone, and recirculating zone.…”

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confidence: 99%

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Base heat flux measurement techniques in impulse hypersonic test facilities

Irimpan

Menezes

Srinivasan

2019

Heat Trans. Asian Res.

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Safe and efficient hypersonic missions require exhaustive testing to capture the surface heat flux used in optimizing thermal protection systems. Though low, base heat transfer rates are still relevant and their estimation is of the utmost importance. Impulse hypersonic test facilities like the shock tunnel are commonly used for such estimation tests. The present paper compares contemporary heat flux measurement techniques, namely, E‐type coaxial thermocouples, Pt‐thin films, and atomic layer thermopiles in a hypersonic shock tunnel at the base of a scaled‐down re‐entry capsule. Base flow establishment is ensured using pressure measurements. The measurements indicated that the base‐stagnation point heat flux was approximately 2% to 3% of the forebody stagnation heat flux and it stabilized at an approximate nondimensional establishment time of 43.2 ± 2.4.

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Section: Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Base heat flux measurement techniques in impulse hypersonic test facilities

Irimpan

Menezes

Srinivasan

2019

Heat Trans. Asian Res.

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“…For an angle of attack lower than 10 • , the heat flux coefficient on the leeward surface is lower than 0.15. Over the years, several heat transfer measurements on a blunt cone model have been reported in the open literature (Steward and Chen (6) , Srinivasan et al (7) ).…”

Section: Introductionmentioning

confidence: 99%

Heat transfer rate and surface pressure measurements in short duration hypersonic flow

et al. 2019

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Experiments were carried out with air as the test gas to obtain the surface convective heating rate and surface pressure distribution on blunt and sharp cone models flying at hypersonic speeds. Tests were performed in a hypersonic shock tunnel at two different angles of attack: ${0}^\circ$ and ${5}^\circ$ with angles of rotation $\phi = {0}^\circ, {90}^\circ$, and ${180}^\circ$. The experiments were conducted at a stagnation enthalpy of 1.4MJ/kg, flow Mach number of 6.56 and free stream Reynolds number based on the model length of $9.1 \times {10}^{5}$. The effective test time of the shock tunnel is 3ms. The results obtained for cone model with a bluntness ratio of 0.2 were compared with sharp cone models for $\alpha ={0}^\circ$. The measured stagnation heat transfer value matched well with the theoretical value predicted by the Fay and Riddell correlation and with the CFD results.

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“…At a ¼ 0 , increasing bluntness ratio reduced heating rate and a > 0 , windward heating rate was higher along the flow direction. Srinivasan et al 4 carried out experiments on crew module where forebody and base heat flux measured in short duration impulse facilities at Vikram Sarabhai Space Centre. The result showed gradual decrease in aerodynamic heating from stagnation point, windward side heating rates increased with angle of attack.…”

Section: Introductionmentioning

confidence: 99%

Convective heat-transfer rate and surface pressure distribution over a cone model at hypersonic speeds

Saiprakash

Senthilkumar

Balu

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article, experiments are carried out in a hypersonic shock tunnel with helium as driver gas and air as the test gas to obtain the convective heating rate and surface pressure distribution on a cone model placed at hypersonic speed. Test is performed in hypersonic shock tunnel for a flow Mach number of 6.5 at two different angles of attack, 0° and 5°. The sputtered thin film platinum sensors are used to measure the heat flux on a cone model. The measured heat-transfer rate compares well with theoretically estimated values using reference enthalpy method and computational fluid dynamics (CFD) simulation. The measured surface pressure compares well with CFD.

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Fore-body and base heat flux measurements on a typical crew module in short duration impulse facilities

Cited by 16 publications

References 35 publications

Base heat flux measurement techniques in impulse hypersonic test facilities

Base heat flux measurement techniques in impulse hypersonic test facilities

Heat transfer rate and surface pressure measurements in short duration hypersonic flow

Convective heat-transfer rate and surface pressure distribution over a cone model at hypersonic speeds

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