Effects of wing sweep on boundary-layer transition for a smooth F-14A wing at Mach numbers from 0.700 to 0.825
By: Bianca Trujillo Anderson and Robert R. Meyer, Jr.
Contributors: Meyer, Robert R.; Dryden Flight Research Facility.
Series: NASA technical memorandum -- 101712.
Publisher: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility; For sale by the National Technical Information Service
Published: 1990
Place of publication: Edwards, Calif; [Springfield, Va
Language: eng
Format: Microform
Subjects: Laminar flow.; Boundary layer transition.; Flow distribution.; Laminar flow.; Mach number.; Variable sweep wings.
Notes: Also available via Internet from the NASA Technical Reports Server web site. Address as of 3/16/05: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19910015243%5F1991015243.pdf; current access is available via PURL.

Microfiche. [Washington, D.C.? : National Aeronautics and Space Administration], 1991. 1 microfiche.