Pressure fields investigation by LPS technology on the aerospacecraft model

A. O. Andreev; A. P. Bukov; M. W. lpatov; S. V. Kabin; P. D. Nushtaev; A. A. Orlov; V. E. Mosharov; V. N. Radchenko; V. K. Pesetsky; S. D. Phonov

doi:doi:10.1051/jp3:1994105

Issue		J. Phys. III France Volume 4, Number 11, November 1994


Page(s)		2317 - 2327
DOI		https://doi.org/10.1051/jp3:1994105

DOI: 10.1051/jp3:1994105
J. Phys. III France 4 (1994) 2317-2327

Pressure fields investigation by LPS technology on the aerospacecraft model

A. O. Andreev, A. P. Bukov, M. W. lpatov, S. V. Kabin, P. D. Nushtaev, A. A. Orlov, V. E. Mosharov, V. N. Radchenko, V. K. Pesetsky and S. D. Phonov

Central Aerohydrodynamic Institute, Zhukovsky, Moscow reg., Russia

(Received 6 April 1993, revised 8 July 1994, accepted 5 August 1994)

Abstract
The results of Luminescence Pressure Sensor (LPS) technology applications for pressure field measurements on the surface of aerospacecraft model $\ll$ BURAN $\gg$ are presented. Physical principles of LPS technology, an experimental technique and data reduction method are considered. A flow around model was investigated at Mach number range $0.85 \div 0.96$ and angles of attack range $8^\circ \div 16^\circ$ .