NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
The influence of laminar separation and transition on low Reynolds number airfoil hysteresisAn experimental study of the Lissaman 7769 and Miley MO6-13-128 airfoils at low chord Reynolds numbers is presented. Although both airfoils perform well near their design Reynolds number of about 600,000, they each produce a different type of hysteresis loop in the lift and drag forces when operated below chord Reynolds numbers of 300,000. The type of hysteresis loop was found to depend upon the relative location of laminar separation and transition. The influence of disturbance environment and experimental procedure on the low Reynolds number airfoil boundary layer behavior is also presented. The use of potential flow solutions to help predict how a given airfoil will behave at low Reynolds numbers is also discussed.
Document ID
19840055223
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mueller, T. J.
(Notre Dame, University Notre Dame, IN, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-1617
Accession Number
84A38010
Funding Number(s)
CONTRACT_GRANT: N00014-83-K-0239
CONTRACT_GRANT: NSG-1419
CONTRACT_GRANT: N00014-81-K-2036
Distribution Limits
Public
Copyright
Other

Available Downloads

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