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Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels by means of a slender wedge probe and direct numerical simulation

Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels by means of a slender wedge probe and direct numerical simulation
Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels by means of a slender wedge probe and direct numerical simulation
Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels were conducted by means of a slender wedge probe and direct numerical simulation. The study comprises comparative tunnel noise measurements at Mach 3, 6 and 7.4 in two Ludwieg tube facilities and a shock tunnel. Surface pressure fluctuations were measured over a wide range of frequencies and test conditions including harsh test environments not accessible to measurement techniques such as Pitot probes and hot-wire anemometry. A good agreement was found between normalized Pitot pressure fluctuations converted into normalized static pressure fluctuations and the wedge probe readings. Quantitative results of the tunnel noise are provided in frequency ranges relevant for hypersonic boundary-layer transition. Complementary numerical simulations of the leading-edge receptivity to fast and slow acoustic waves were performed for the applied wedge probe at conditions corresponding to the experimental free-stream conditions. The receptivity to fast acoustic waves was found to be characterized by an early amplification of the induced fast mode. For slow acoustic waves an initial decay was found close to the leading edge. At all Mach numbers, and for all considered frequencies, the leading-edge receptivity to fast acoustic waves was found to be higher than the receptivity to slow acoustic waves. Further, the effect of inclination angles of the acoustic wave with respect to the flow direction was investigated. An inclination angle was found to increase the response on the wave-facing surface of the probe and decrease the response on the opposite surface for fast acoustic waves. A frequency-dependent response was found for slow acoustic waves. The combined numerical and experimental approach in the present study confirmed the previous suggestion that the slow acoustic wave is the dominant acoustic mode in noisy hypersonic wind tunnels.
0022-1120
495-531
Wagner, Alexander
45ad75dc-38e7-4be9-88fd-6fce0baf4fca
Schulein, Erich
af733a2c-9539-4379-b7d6-1181014c2a61
Petervari, Rene
f8b1517c-8ad3-483f-aab9-b0d40406f0ca
Hannemann, Klaus
d12f3114-1e91-424f-99fa-65dd5ab94254
Ali, Syed R.C.
343f886c-609d-48ae-9068-1ca36144f798
Cerminara, Adriano
6fd11181-c852-4558-82b5-5f7eac291a3f
Sandham, Neil D.
0024d8cd-c788-4811-a470-57934fbdcf97
Wagner, Alexander
45ad75dc-38e7-4be9-88fd-6fce0baf4fca
Schulein, Erich
af733a2c-9539-4379-b7d6-1181014c2a61
Petervari, Rene
f8b1517c-8ad3-483f-aab9-b0d40406f0ca
Hannemann, Klaus
d12f3114-1e91-424f-99fa-65dd5ab94254
Ali, Syed R.C.
343f886c-609d-48ae-9068-1ca36144f798
Cerminara, Adriano
6fd11181-c852-4558-82b5-5f7eac291a3f
Sandham, Neil D.
0024d8cd-c788-4811-a470-57934fbdcf97

Wagner, Alexander, Schulein, Erich, Petervari, Rene, Hannemann, Klaus, Ali, Syed R.C., Cerminara, Adriano and Sandham, Neil D. (2018) Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels by means of a slender wedge probe and direct numerical simulation. Journal of Fluid Mechanics, 842, 495-531. (doi:10.1017/jfm.2018.132).

Record type: Article

Abstract

Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels were conducted by means of a slender wedge probe and direct numerical simulation. The study comprises comparative tunnel noise measurements at Mach 3, 6 and 7.4 in two Ludwieg tube facilities and a shock tunnel. Surface pressure fluctuations were measured over a wide range of frequencies and test conditions including harsh test environments not accessible to measurement techniques such as Pitot probes and hot-wire anemometry. A good agreement was found between normalized Pitot pressure fluctuations converted into normalized static pressure fluctuations and the wedge probe readings. Quantitative results of the tunnel noise are provided in frequency ranges relevant for hypersonic boundary-layer transition. Complementary numerical simulations of the leading-edge receptivity to fast and slow acoustic waves were performed for the applied wedge probe at conditions corresponding to the experimental free-stream conditions. The receptivity to fast acoustic waves was found to be characterized by an early amplification of the induced fast mode. For slow acoustic waves an initial decay was found close to the leading edge. At all Mach numbers, and for all considered frequencies, the leading-edge receptivity to fast acoustic waves was found to be higher than the receptivity to slow acoustic waves. Further, the effect of inclination angles of the acoustic wave with respect to the flow direction was investigated. An inclination angle was found to increase the response on the wave-facing surface of the probe and decrease the response on the opposite surface for fast acoustic waves. A frequency-dependent response was found for slow acoustic waves. The combined numerical and experimental approach in the present study confirmed the previous suggestion that the slow acoustic wave is the dominant acoustic mode in noisy hypersonic wind tunnels.

Text
combined_freestream_disturbance_measurements_and_receptivity_studies_in_hypersonic_wind_tunnels_by_means_of_a_slender_wedge_probe_and_direct_numerical_simulation - Version of Record
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Accepted/In Press date: 25 January 2018
e-pub ahead of print date: 13 March 2018
Published date: 10 May 2018

Identifiers

Local EPrints ID: 419232
URI: http://eprints.soton.ac.uk/id/eprint/419232
ISSN: 0022-1120
PURE UUID: ad540e6a-4fc7-4d00-8f2e-7350d435fce1
ORCID for Neil D. Sandham: ORCID iD orcid.org/0000-0002-5107-0944

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Date deposited: 09 Apr 2018 16:30
Last modified: 07 Oct 2020 01:42

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