Application of hot-wire technology in a slowdown type transonic wind tunnel

V. Zinoviev, V. Lebiga, Kung-Ming Chung, Jiun-Jih Miau

Research output: Contribution to conferencePaper

Abstract

The application of the multiple overheats method for measuring of the intensity and the spectral composition of the fluctuation characteristics in wind tunnels with limited running time is considered. Peculiarities of the hot-wire technique in operation for transonic wind tunnel are discussed. By using the technique proposed in this paper, the intensity of the mass flow and total temperature fluctuations, correlation coefficients and their frequency spectra at the free-stream Mach numbers M = 0.4, 0.6, 0.76 were obtained. It is shown that the acoustic fluctuations are predominant in the flow at all Mach numbers under the study.

Original languageEnglish
Publication statusPublished - 2001 Dec 1
Event39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States
Duration: 2001 Jan 82001 Jan 11

Other

Other39th Aerospace Sciences Meeting and Exhibit 2001
CountryUnited States
CityReno, NV
Period01-01-0801-01-11

Fingerprint

transonic wind tunnels
wind tunnel
Mach number
Wind tunnels
wire
Wire
acoustics
Acoustics
mass flow
free flow
wind tunnels
correlation coefficients
Chemical analysis
temperature
Temperature

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Zinoviev, V., Lebiga, V., Chung, K-M., & Miau, J-J. (2001). Application of hot-wire technology in a slowdown type transonic wind tunnel. Paper presented at 39th Aerospace Sciences Meeting and Exhibit 2001, Reno, NV, United States.
Zinoviev, V. ; Lebiga, V. ; Chung, Kung-Ming ; Miau, Jiun-Jih. / Application of hot-wire technology in a slowdown type transonic wind tunnel. Paper presented at 39th Aerospace Sciences Meeting and Exhibit 2001, Reno, NV, United States.
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Zinoviev, V, Lebiga, V, Chung, K-M & Miau, J-J 2001, 'Application of hot-wire technology in a slowdown type transonic wind tunnel' Paper presented at 39th Aerospace Sciences Meeting and Exhibit 2001, Reno, NV, United States, 01-01-08 - 01-01-11, .

Application of hot-wire technology in a slowdown type transonic wind tunnel. / Zinoviev, V.; Lebiga, V.; Chung, Kung-Ming; Miau, Jiun-Jih.

2001. Paper presented at 39th Aerospace Sciences Meeting and Exhibit 2001, Reno, NV, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Application of hot-wire technology in a slowdown type transonic wind tunnel

AU - Zinoviev, V.

AU - Lebiga, V.

AU - Chung, Kung-Ming

AU - Miau, Jiun-Jih

PY - 2001/12/1

Y1 - 2001/12/1

N2 - The application of the multiple overheats method for measuring of the intensity and the spectral composition of the fluctuation characteristics in wind tunnels with limited running time is considered. Peculiarities of the hot-wire technique in operation for transonic wind tunnel are discussed. By using the technique proposed in this paper, the intensity of the mass flow and total temperature fluctuations, correlation coefficients and their frequency spectra at the free-stream Mach numbers M = 0.4, 0.6, 0.76 were obtained. It is shown that the acoustic fluctuations are predominant in the flow at all Mach numbers under the study.

AB - The application of the multiple overheats method for measuring of the intensity and the spectral composition of the fluctuation characteristics in wind tunnels with limited running time is considered. Peculiarities of the hot-wire technique in operation for transonic wind tunnel are discussed. By using the technique proposed in this paper, the intensity of the mass flow and total temperature fluctuations, correlation coefficients and their frequency spectra at the free-stream Mach numbers M = 0.4, 0.6, 0.76 were obtained. It is shown that the acoustic fluctuations are predominant in the flow at all Mach numbers under the study.

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M3 - Paper

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Zinoviev V, Lebiga V, Chung K-M, Miau J-J. Application of hot-wire technology in a slowdown type transonic wind tunnel. 2001. Paper presented at 39th Aerospace Sciences Meeting and Exhibit 2001, Reno, NV, United States.