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Effects of Wing Sweep on Boundary-layer Transition for a Smooth F-14A Wing at Mach Numbers from 0.700 to 0.825The results are discussed of the variable sweep transition flight experiment (VSTFE). The VSTFE was a natural laminar flow experiment flown on the swing wing F-14A aircraft. The main objective of the VSTFE was to determine the effects of wing sweep on boundary layer transition at conditions representative of transport aircraft. The experiment included the flight testing of two laminar flow wing gloves. Glove 1 was a cleanup of the existing F-14A wing. Glove 2, not discussed herein, was designed to provide favorable pressure distributions for natural laminar flow at Mach number (M) 0.700. The transition locations presented for glove 1 were determined primarily by using hot film sensors. Boundary layer rake data was provided as a supplement. Transition data were obtained for leading edge wing sweeps of 15, 20, 25, 30, and 35 degs, with Mach numbers ranging from 0.700 to 0.825, and 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 of 13.7 x 10(exp 6) was obtained for the condition of 15 deg of sweep, M = 0.800, and an altitude of 20,000 ft.
Document ID
19910015243
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
May 1, 1990
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-101712
H-1531
NAS 1.15:101712
Accession Number
91N24556
Funding Number(s)
PROJECT: RTOP 505-60-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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