NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Measurements of the boundary layer and near wake of a supercritical airfoil at cruise conditionsThe flow behavior within the upper-surface boundary layer and near wake of a supercritical airfoil operating at cruise conditions is discussed. Experimental results obtained from wind-tunnel tests are presented which provide a more detailed description of the flow in these regions than was previously available. Mean streamwise velocity profiles measured by pitot-pressure-probe and laser-velocimeter techniques were found to be in excellent agreement. Other mean-flow properties obtained by the laser-velocimeter technique were the local flow angles in the viscous layers and the static pressures at the edges of the boundary layer and wake. The data set also includes measurements of the turbulence intensity and turbulent Reynolds-stress distributions as obtained by the laser-velocimeter technique. To assess the effects of the shock wave, a less extensive set of measurements was realized at a subcritical test condition. The two test conditions (Mach number at free-stream conditions = 0.72, airfoil section lift coefficient = 0.76 and Mach number of free-stream conditions = 0.5, airfoil section lift coefficient = 0.75) provide a good test for state-of-the-art prediction methods because the upper-surface-boundary layer is separated just upstream of the trailing edge in both cases.
Document ID
19810061486
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johnson, D. A.
(NASA Ames Research Center Moffett Field, CA, United States)
Spaid, F. W.
(McDonnell Douglas Research Laboratories St. Louis, MO, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 81-1242
Meeting Information
Meeting: Fluid and Plasma Dynamics Conference
Location: Palo Alto, CA
Start Date: June 23, 1981
End Date: June 25, 1981
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
81A45890
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available