Pitch Rate and Reynolds Number Effects on Unsteady Boundary-Layer Transition and Separation-Reference-Cited by-同舟云学术

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Pitch Rate and Reynolds Number Effects on Unsteady Boundary-Layer Transition and Separation

Published:1998-01 Issue:1 Volume:35 Page:46-52
ISSN:0021-8669
Container-title:Journal of Aircraft
language:en
Short-container-title:Journal of Aircraft

Author:

Schreck Scott J.¹,Faller William E.²,Helin Hank E.³

Affiliation:

1. U.S. Air Force Office of Scientific Research, Bolling Air Force Base, Washington, D.C. 20332

2. Johns Hopkins University, Baltimore, Maryland 21218

3. U.S. Air Force Operational Test and Evaluation Center, Kirtland Air Force Base, New Mexico 87117

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/2.2258

Reference18 articles.

1. Progress in analysis and prediction of dynamic stall

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2. Dynamic responses of pitching hydrofoil in laminar–turbulent transition regime;Journal of Fluids and Structures;2022-05

3. Surface Roughness Effects on Unsteady Transition Property over a Pitching Airfoil;Journal of Aerospace Engineering;2022-05

4. An experimental study on boundary layer transition detection over a pitching supercritical airfoil using hot-film sensors;International Journal of Heat and Fluid Flow;2020-12

5. Infrared thermography for boundary layer transition measurements;Measurement Science and Technology;2020-09-25

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