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

Abstract

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.

Investigation of the separated region ahead of three-dimensional protuberances on plates and cones in hypersonic flows with laminar boundary layers

“…The heat transfer process in these gauges is modeled using a semi-infinite, one-dimensional assumption. 27 The thickness of the macor should be several orders higher than that of the platinum film. The heat penetration depth is directly proportional to the square root of the thermal diffusivity of the substrate and the effective test time of the experiment.…”

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

“…Most of the literature results have been obtained in HDST2. This shock-tunnel has been extensively used for investigating hypersonic flow-field and aeroheating around blunt bodies during re-entry [139][140][141] and missiles [142]. Scramjet studies have been carried out in HDST2 [137,143].…”

Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds

“…Macor is a good ceramic substrate for this purpose since it behaves like a perfect insulator to temperatures as high as 800 °C, apart from being hard and machinable. Thickness of the substrate is a very important parameter in the measurement of heat flux [16]. One-dimensional heat conduction equation is used to simulate the heat transfer process in the gauges.…”