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Titolo:
APPLICATION OF PRESSURE-SENSITIVE PAINT IN SUPERSONIC NOZZLE RESEARCH
Autore:
CLER D; LAMB M; FAROKHI S; TAGHAVI R; HAZLEWOOD R;
Indirizzi:
NASA,LANGLEY RES CTR,RES FACIL BRANCH HAMPTON VA 23681
Titolo Testata:
Journal of aircraft
fascicolo: 6, volume: 33, anno: 1996,
pagine: 1109 - 1114
SICI:
0021-8669(1996)33:6<1109:AOPPIS>2.0.ZU;2-W
Fonte:
ISI
Lingua:
ENG
Tipo documento:
Article
Natura:
Periodico
Settore Disciplinare:
Science Citation Index Expanded
Citazioni:
17
Recensione:
Indirizzi per estratti:
Citazione:
D. Cler et al., "APPLICATION OF PRESSURE-SENSITIVE PAINT IN SUPERSONIC NOZZLE RESEARCH", Journal of aircraft, 33(6), 1996, pp. 1109-1114

Abstract

An experimental study was conducted to evaluate the pressure-sensitive paint (PSP) technique as a means of obtaining global surface pressure distribution on the inside surface of a supersonic nozzle at NASA Langley Research Center, In this experiment, the PSP technique was used to measure the surface pressure distribution for several configurations of a convergent-divergent nozzle, which was also instrumented with adensely packed array of pressure taps. The PSP and pressure tap data were obtained simultaneously for each configuration of the nozzle, at several nozzle pressure ratios, to determine the effects of supersoniccavity-ramp vortex generators on the nozzle now and performance, Results from the PSP data agreed very well with the pressure tap data and indicated that a pair of counter-rotating vortices were shed from the cavity vortex generator, The presence of these streamwise vortices caused a delay in the formation of the shock wave inside the nozzle.

ASDD Area Sistemi Dipartimentali e Documentali, Università di Bologna, Catalogo delle riviste ed altri periodici
Documento generato il 02/12/20 alle ore 05:17:20