Hypersonic, turbulent, cold-wall, skin-friction and heat-transfer measurements on an axisymmetric sharp cone

Abstract

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Optimal heat flux for delaying transition to turbulence in a high-speed boundary layer

“…While an instantaneous wall temperature T wall /T ∞ ≈ 0.4 (T wall /T ad ≈ 0.1) is small, it is not unlike values reported in laboratory experiments (see e.g. Wallace 1967;Chien 1973). In terms of the commonly reported ratio of the mean wall-temperature to the adiabatic value, at the final iteration this quantity has the range 0.37 ≤T wall /T ad ≤ 1.12, which is comparable to previous studies (Lysenko & Maslov 1984;Fedorov et al 2015;Bountin et al 2018).…”

Methodology for Turbulence Model Validation: Application to Hypersonic Flows

“…The earlier database for sharp cones has been reviewed by Bertin et al 20 One of the earlier wind-tunnel investigations on the skin friction and heat transfer on a sharp cone at a freestream Mach number of 7.9 was performed by Chien. 21 A published workshop edited by by Desideri et al 22 used the sharp cone as one of the hypersonicturbulent ow problemsto be solved by participants. The original data for the problem have been developed further with the data obtained in the Imperial College number 2 gun tunnel at a Mach number of 9.26.…”

Hypersonic, Turbulent S kin-F riction and Heat-Transfer Measurements on a Sharp Cone

“…Pictures showing the setup, the model, and the balances, and typical calibration results can be found in Ref. 21. Based on a least-squares linear fit, the balance proved to be linear within about 0.3%.…”

“…21. The Thomas-Fitzsimmons initial-lateralconduction-correction method 22 was then applied to the data block of h m to yield a heat-transfer coefficient at time zero, the time at which aerodynamic heating began.…”