Investigation on separated and unseparated transonic convex-corner flows

Research output: Contribution to conferencePaper

Abstract

A naturally developed turbulent boundary layer past convex comers was studied. Mean surface pressure in Mach 0.64 and 0.83 indicated strong inviscid-viscous interactions. Interaction region increased with Mach number and convex-comer angle. Also, unsteadiness of the interactions was characterized by an intermittent region and local peak pressure fluctuation, which was due to the amplification of lower frequency components as shown in power spectra. At higher convex-comer angle (M = 0.83 and α = 15°) the boundary layer was separated. Unsteady shock motion induced intense surface pressure fluctuation which spectrum was centered at about 780 Hz.

Original languageEnglish
Publication statusPublished - 2000 Dec 1
Event38th Aerospace Sciences Meeting and Exhibit 2000 - Reno, NV, United States
Duration: 2000 Jan 102000 Jan 13

Other

Other38th Aerospace Sciences Meeting and Exhibit 2000
CountryUnited States
CityReno, NV
Period00-01-1000-01-13

Fingerprint

corner flow
transonic flow
surface pressure
turbulent boundary layer
Mach number
Boundary layers
amplification
boundary layer
interactions
Power spectrum
Amplification
power spectra
boundary layers
shock
low frequencies

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Chung, K-M. (2000). Investigation on separated and unseparated transonic convex-corner flows. Paper presented at 38th Aerospace Sciences Meeting and Exhibit 2000, Reno, NV, United States.
Chung, Kung-Ming. / Investigation on separated and unseparated transonic convex-corner flows. Paper presented at 38th Aerospace Sciences Meeting and Exhibit 2000, Reno, NV, United States.
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note = "38th Aerospace Sciences Meeting and Exhibit 2000 ; Conference date: 10-01-2000 Through 13-01-2000",

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Chung, K-M 2000, 'Investigation on separated and unseparated transonic convex-corner flows' Paper presented at 38th Aerospace Sciences Meeting and Exhibit 2000, Reno, NV, United States, 00-01-10 - 00-01-13, .

Investigation on separated and unseparated transonic convex-corner flows. / Chung, Kung-Ming.

2000. Paper presented at 38th Aerospace Sciences Meeting and Exhibit 2000, Reno, NV, United States.

Research output: Contribution to conferencePaper

TY - CONF

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PY - 2000/12/1

Y1 - 2000/12/1

N2 - A naturally developed turbulent boundary layer past convex comers was studied. Mean surface pressure in Mach 0.64 and 0.83 indicated strong inviscid-viscous interactions. Interaction region increased with Mach number and convex-comer angle. Also, unsteadiness of the interactions was characterized by an intermittent region and local peak pressure fluctuation, which was due to the amplification of lower frequency components as shown in power spectra. At higher convex-comer angle (M∞ = 0.83 and α = 15°) the boundary layer was separated. Unsteady shock motion induced intense surface pressure fluctuation which spectrum was centered at about 780 Hz.

AB - A naturally developed turbulent boundary layer past convex comers was studied. Mean surface pressure in Mach 0.64 and 0.83 indicated strong inviscid-viscous interactions. Interaction region increased with Mach number and convex-comer angle. Also, unsteadiness of the interactions was characterized by an intermittent region and local peak pressure fluctuation, which was due to the amplification of lower frequency components as shown in power spectra. At higher convex-comer angle (M∞ = 0.83 and α = 15°) the boundary layer was separated. Unsteady shock motion induced intense surface pressure fluctuation which spectrum was centered at about 780 Hz.

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M3 - Paper

ER -

Chung K-M. Investigation on separated and unseparated transonic convex-corner flows. 2000. Paper presented at 38th Aerospace Sciences Meeting and Exhibit 2000, Reno, NV, United States.