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Pressure distribution for the wing of the YAV-8B airplane; with and without pylonsPressure distribution data have been obtained in flight at four span stations on the wing panel of the YAV-8B airplane. Data obtained for the supercritical profiled wing, with and without pylons installed, ranged from Mach 0.46 to 0.88. The altitude ranged from approximately 20,000 to 40,000 ft and the resultant Reynolds numbers varied from approximately 7.2 million to 28.7 million based on the mean aerodynamic chord. Pressure distribution data and flow visualization results show that the full-scale flight wing performance is compromised because the lower surface cusp region experiences flow separation for some important transonic flight conditions. This condition is aggravated when local shocks occur on the lower surface of the wing (mostly between 20 and 35 percent chord) when the pylons are installed for Mach 0.8 and above. There is evidence that convex fairings, which cover the pylon attachment flanges, cause these local shocks. Pressure coefficients significantly more negative than those for sonic flow also occur farther aft on the lower surface (near 60 percent chord) whether or not the pylons are installed for Mach numbers greater than or equal to 0.8. These negative pressure coefficient peaks and associated local shocks would be expected to cause increasing wave and separation drag at transonic Mach number increases.
Document ID
19930005262
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Saltzman, Edwin J. (PRC Kentron, Inc. Edwards, CA., United States)
Delfrate, John H. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Sabsay, Catherine M. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Yarger, Jill M. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:4429
NASA-TM-4429
H-1708
Accession Number
93N14451
Funding Number(s)
PROJECT: RTOP 505-59-53
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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