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Effects of Wing Sweep on In-flight Boundary-layer Transition for a Laminar Flow Wing at Mach Numbers from 0.60 to 0.79The variable sweep transition flight experiment (VSTFE) was conducted on an F-14A variable sweep wing fighter to examine the effect of wing sweep on natural boundary layer transition. Nearly full span upper surface gloves, extending to 60 percent chord, were attached to the F-14 aircraft's wings. The results are presented of the glove 2 flight tests. Glove 2 had an airfoil shape designed for natural laminar flow at a wing sweep of 20 deg. Sample pressure distributions and transition locations are presented with the complete results tabulated in a database. Data were obtained at wing sweeps of 15, 20, 25, 30, and 35 deg, at Mach numbers ranging from 0.60 to 0.79, and at altitudes ranging from 10,000 to 35,000 ft. Results show that a substantial amount of laminar flow was maintained at all the wing sweeps evaluated. The maximum transition Reynolds number obtained was 18.6 x 10(exp 6) at 15 deg of wing sweep, Mach 0.75, and at an altitude of 10,000 ft.
Document ID
19910015242
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Anderson, Bianca Trujillo (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Meyer, Robert R., Jr. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1990
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
H-1565
NAS 1.15:101701
NASA-TM-101701
Accession Number
91N24555
Funding Number(s)
PROJECT: RTOP 505-60-4X
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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