NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Experimental transition and boundary-layer stability analysis for a slotted swept laminar flow control airfoilA swept, supercritical laminar flow control (LFC) airfoil designated NASA SCLFC(1)-0513F was tested at subsonic and transonic speeds in the NASA Langley eight-foot Transonic Pressure Tunnel. This paper examines Tollmien-Schlichting and crossflow disturbance amplification for this airfoil using the linear stability method. The design methodology using linear stability analysis is evaluated and the results of the incompressible and compressible methods are compared. Experimental data on the swept, supercritical LFC airfoil and reference wind tunnel and flight results are used to correlate and evaluate the N-factor method for transition prediction over a speed range M(infinity) from zero to one.
Document ID
19900029738
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Harvey, William D.
(NASA Langley Research Center Hampton, VA, United States)
Harris, Charles D.
(NASA Langley Research Center Hampton, VA, United States)
Brooks, Cuyler W., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aerodynamics
Accession Number
90A16793
Distribution Limits
Public
Copyright
Other

Available Downloads

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