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KC-135 wing and winglet flight pressure distributions, loads, and wing deflection results with some wind tunnel comparisonsA full-scale winglet flight test on a KC-135 airplane with an upper winglet was conducted. Data were taken at Mach numbers from 0.70 to 0.82 at altitudes from 34,000 feet to 39,000 feet at stabilized flight conditions for wing/winglet configurations of basic wing tip, 15/-4 deg, 15/-2 deg, and 0/-4 deg winglet cant/incidence. An analysis of selected pressure distribution and data showed that with the basic wing tip, the flight and wind tunnel wing pressure distribution data showed good agreement. With winglets installed, the effects on the wing pressure distribution were mainly near the tip. Also, the flight and wind tunnel winglet pressure distributions had some significant differences primarily due to the oilcanning in flight. However, in general, the agreement was good. For the winglet cant and incidence configuration presented, the incidence had the largest effect on the winglet pressure distributions. The incremental flight wing deflection data showed that the semispan wind tunnel model did a reasonable job of simulating the aeroelastic effects at the wing tip. The flight loads data showed good agreement with predictions at the design point and also substantiated the predicted structural penalty (load increase) of the 15 deg cant/-2 deg incidence winglet configuration.
Document ID
19840019620
Document Type
Conference Paper
Authors
Montoya, L. C.
(NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Jacobs, P.
(NASA Langley Research Center Va., United States)
Flechner, S.
(NASA Langley Research Center Va., United States)
Sims, R.
(NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1982
Publication Information
Publication: KC-135 Winglet Program Rev.
Subject Category
Aerodynamics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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