S. V. Bobashev, N. P. Mende, P. A. Popov, B. I. Reznikov, V. A. Sakharov, S. Z. Sapozhnikov, V. Yu. Mityakov, A. V. Mityakov, D. A. Bountin, A. A. Maslov, H. Knauss, T. Roediger, “Using anisotropic heat flux sensors in aerodynamic experiments”, Pisma v Zhurnal Tekhnicheskoi Fiziki, 2009, Volume 35, Issue 5,Pages <nobr>36

This article is cited in 10 papers

Using anisotropic heat flux sensors in aerodynamic experiments

S. V. Bobashev^a, N. P. Mende^a, P. A. Popov^a, B. I. Reznikov^a, V. A. Sakharov^a, S. Z. Sapozhnikov^b, V. Yu. Mityakov^b, A. V. Mityakov^b, D. A. Bountin^c, A. A. Maslov^c, H. Knauss^d, T. Roediger^d

^a Ioffe Institute, St. Petersburg
^b St. Petersburg Polytechnic University
^c Institute of Theoretical and Applied Mechanics, Siberian Branch of the Russian Academy of Sciences, Novosibirsk
^d Institut fur Aero- und Gasdynamik (IAG), Universitat Stuttgart, 70569, Stuttgart, Germany

Abstract: We present the results of comparative measurements of the heat flux to a flat plate in a supersonic flow at a Mach number of M = 6, which were performed using the two following anisotropic heat sensors with different thicknesses of sensor elements: (i) Atomic Layer Thermo Pile (ALTP, Fortech GmbH, Germany) with a thickness of $\sim$0.5 $\times$ 10$^{-4}$ m and (ii) gradient heat flux sensor (GHFS, St. Petersburg State Polytechnic University, Russia) with a thickness of $\sim$2 $\times$ 10$^{-4}$ m. The ALTP sensor can be used for directly measuring heat fluxes in processes with a characteristic time above 10$^{-6}$ s. A method for mathematically processing the GHFS response signal is proposed that allows heat flux oscillations to be revealed in gasdynamic process with a characteristic time on the order of 10$^{-4}$ s.

Received: 23.10.2008