NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
A Wind Tunnel Experiment for Trailing Edge Circulation Control on a 6 Percent 2-D Airfoil up to Transonic Mach NumbersA wind tunnel test was conducted on a six percent thick slightly cambered elliptical circulation control airfoil with both upper and lower surface blowing. Parametric evaluations of jet slot heights and Coanda surface shapes were conducted at mass flow coefficients (C(sub mu)) from 0.0 to 0.12. The test data was acquired in the NASA Langley Transonic Dynamics Tunnel at Mach numbers of 0.8 and 0.3 at Reynolds numbers per foot of 1.05 x 10(exp 6) and 2.43 x 10(exp 5) respectively. For the transonic condition, (Mach = 0.8 at alpha = +3 deg), it was generally found that the smaller slot and larger Coanda surface were more effective overall than other slot/Coanda surface combinations. Generally it was found at Mach = 0.3 at alpha = 6 deg that the smaller slot and smaller Coanda surface were more effective overall than other slot/Coanda surface combinations.
Document ID
20050192636
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Alexander, Michael G.
(NASA Langley Research Center Hampton, VA, United States)
Anders, Scott G.
(NASA Langley Research Center Hampton, VA, United States)
Johnson, Stuart K.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
June 1, 2005
Publication Information
Publication: Proceedings of the 2004 NASA/ONR Circulation Control Workshop, Part 1
Subject Category
Engineering (General)
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available