Hot-wire measurements of compressor blade wakes in a cascade wind tunnel
By: Adem Baydar
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1988
Place of publication: Monterey, California
Language: eng
Number of pages: 47
Subjects: Aeronautics
Description: A hot-wire system, with software designed for calibrating and taking data with single, double and triple hot-wire sensors separately, or three probes at once, was verified and used to make wake measurements downstream of a compressor stator blade in a cascade wind tunnel. Using a single hot-wire probe, velocity and turbulence data were obtained in the wake of the controlled-diffusion blade in order to verify LDV data taken in earlier studies. The tests were conducted at three inlet angles from near design incidence towards the expected stall condition at a Mach number of 0.25 and Reynolds number of about 700,000. Wake profiles were obtained from 0.08 to 0.2 chord lengths downstream of the blade. Good agreement was found with LDV measurements. Measurements at the highest incidence angle showed that the wake constituted one third of the flow and yet no separation occurred before the trailing edge on the suction side of the blade. Keywords: Laser doppler velocimeters.
Notes: Thesis advisor(s): Shreeve, Raymond P.

"March 1988."

Thesis (M.S. in A.E)--Naval Postgraduate School, March 1988.

Includes bibliographical references.

Approved for public release, distribution ulimited.