NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
A supercritical airfoil experimentThe purpose of this investigation is to provide a comprehensive data base for the validation of numerical simulations. The objective of the present paper is to provide a tabulation of the experimental data. The data were obtained in the two-dimensional, transonic flowfield surrounding a supercritical airfoil. A variety of flows were studied in which the boundary layer at the trailing edge of the model was either attached or separated. Unsteady flows were avoided by controlling the Mach number and angle of attack. Surface pressures were measured on both the model and wind tunnel walls, and the flowfield surrounding the model was documented using a laser Doppler velocimeter (LDV). Although wall interference could not be completely eliminated, its effect was minimized by employing the following techniques. Sidewall boundary layers were reduced by aspiration, and upper and lower walls were contoured to accommodate the flow around the model and the boundary-layer growth on the tunnel walls. A data base with minimal interference from a tunnel with solid walls provides an ideal basis for evaluating the development of codes for the transonic speed range because the codes can include the wall boundary conditions more precisely than interference connections can be made to the data sets.
Document ID
19960047577
Acquisition Source
Ames Research Center
Document Type
Other
Authors
Mateer, G. G.
(NASA Ames Research Center Moffett Field, CA United States)
Seegmiller, H. L.
(NASA Ames Research Center Moffett Field, CA United States)
Hand, L. A.
(NASA Ames Research Center Moffett Field, CA United States)
Szodruck, J.
(Messerschmitt-Boelkow-Blohm G.m.b.H. Bremen, Germany)
Date Acquired
August 17, 2013
Publication Date
January 1, 1994
Subject Category
Aerodynamics
Report/Patent Number
OTN-035236
OTN-BIBL-AGARD-AR-303-Vol-2
Accession Number
96N72680
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

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