NASA-TP-1919
Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section
Note:
This document has not been validated by ESDU. It is provided to our users as a useful reference source.
Abstract:
Wind-tunnel tests were conducted in the Langley low-turbulence pressure tunnel to evaluate the effects on performance of modifying a 17-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the pitching-moment coefficient by increasing the forward loading and to increase the climb lift-drag ratio by decreasing the aft upper surface pressure gradient. The tests were conducted over a Mach number range from 0.07 to 0.32, a chord Reynolds number range 1.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle-of-attack range from about -10 deg to 20 deg.
Author(s):
R.J. McGhee; W.D. Beaseley
Indexed under:
- None
Details:
NASA-TP-1919 | |
---|---|
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.