Supercritical airfoil drag reduction by passive shock wave/boundary layer control in the Mach number range .75 to .90-Reference-Cited by-同舟云学术

Supercritical airfoil drag reduction by passive shock wave/boundary layer control in the Mach number range .75 to .90

Published:1985-01-14 Issue: Volume: Page:
ISSN:
Container-title:23rd Aerospace Sciences Meeting
language:
Short-container-title:

Author:

NAGAMATSU H.¹,FICARRA R.²

Affiliation:

1. Rensselaer Polytechnic Institute, Troy, NY

2. Grumman Aerospace Corp., Bethpage, NY

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1985-207

Reference13 articles.

1. Bahi, L. "Passive ShockWaveIBounaary Layer Control for Transonic Supercritical Airfoil Drag Reduction," Ph.D. Thesis,RensselaerPolytechnic Institute, Troy, NewPork,May 1982.

2. Ross, J. "Passive Shock WaveIBoundary Layer Control for Drag Reduction on a Convex Transonic Airfoil," M.S. Thesis,Rensselaer Polytechnic Institute, Troy, NewYork,May 1982.

3. Bidlack, T. "Top Wall Blockage Effects on Passive Shock WavelBotmndury Layer Control for a Supercritical Airfoil," M.S. Thesis,Rensselaer PolytechnicInstitute, Troy, NewYork,August 1982.

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