NASA-TM-X-74018
Low-speed wind tunnel results for a modified 13-percent-thick airfoil
Note:
This document has not been validated by ESDU. It is provided to our users as a useful reference source.
Abstract:
Abstract: Wind-tunnel tests were conducted to evaluate the effects on performance of modifying a 13-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the aft upper surface pressure gradient and hence delay boundary layer separation at typical lift coefficients for light general aviation airplanes. The tests were conducted at a Mach number of 0.15 or less over a Reynolds number range from about 1,000,000 to 9,000,000.
Author(s):
R.J. McGhee; W.D. Beasley
Indexed under:
- None
Details:
NASA-TM-X-74018 | |
---|---|
Format: |
|
Status: |
|
Previous Releases: |
|
The document you have requested is available only to subscribers.
- Subscribers login here.
- If you are not an ESDU subscriber find out how to subscribe.