热科学学报（英文版）2003，Vol.12Issue(1)：44-50,7.
Skin Friction Gage for Measurements in Hypersonic Flow
Skin Friction Gage for Measurements in Hypersonic Flow
Francois Falempin 1Marat Goldfeld 2Roman Nestoulia2
作者信息
- 1. EADS Aerospatiale Matra Missiles, Chatillon, France
- 2. Institute of Theoretical and Applied Mechanics, Novosibirsk, Russia
- 折叠
摘要
Abstract
A description and results of tests of a new small-scale gage for direct measurement of skin friction force are presented in the paper. The gage design provides separated measurement of longitudinal and transversal component of friction force. Application of this scheme provides high sensitivity and necessary high-frequency response of the gage. The tests of the gage were carried out in a blow down wind tunnel at Mach numbers of 2 and 4 within the range of Reynolds numbers Rex from 0.8 to 5 million and in the hot-shot wind tunnel at Mach number 6 and Reynolds numbers Rex= 2.5-10 million. The measurements of skin friction were carried out on a flat plate and on a ramp beyond the shock wave. Simultaneously with the direct measurement of friction in the blow down wind tunnel, the measurements of profiles of average velocities and mass flow rate pulsations were realised. Analysis of measurement errors has shown that the friction gage permits to measure skin friction coefficient on a flat plate with mistake not more than 10%.关键词
skin friction gage/hypersonic flow/scramjetKey words
skin friction gage/hypersonic flow/scramjet分类
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Francois Falempin,Marat Goldfeld,Roman Nestoulia..Skin Friction Gage for Measurements in Hypersonic Flow[J].热科学学报（英文版）,2003,12(1):44-50,7.
