Hostname: page-component-78c5997874-fbnjt Total loading time: 0 Render date: 2024-11-04T09:13:32.850Z Has data issue: false hasContentIssue false
  • English
  • Français

Wind tunnel testing of powered lift, all-wing STOL model

Published online by Cambridge University Press:  03 February 2016

S. W. Collins ,
B. W. Westra ,
J. C. Lin ,
G. S. Jones  and
C. H. Zeune
S. W. Collins
Affiliation:
[email protected], Northrop Grumman Corporation, El Segundo California, USA
B. W. Westra
Affiliation:
[email protected], Northrop Grumman Corporation, El Segundo California, USA
J. C. Lin
Affiliation:
NASA Langley Research Center, Hampton, Virginia, USA
G. S. Jones
Affiliation:
NASA Langley Research Center, Hampton, Virginia, USA
C. H. Zeune
Affiliation:
Air Force Research Laboratory, Wright-Patterson AFB, Ohio, USA
Get access Rights & Permissions [Opens in a new window]

Abstract

Short take-off and landing (STOL) systems can offer significant capabilities to warfighters and, for civil operators thriving on maximising efficiencies they can improve airspace use while containing noise within airport environments. In order to provide data for next generation systems, a wind tunnel test of an all-wing cruise efficient, short take-off and landing (CE STOL) configuration was conducted in the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) 14ft by 22ft Subsonic Wind Tunnel. The test’s purpose was to mature the aerodynamic aspects of an integrated powered lift system within an advanced mobility configuration capable of CE STOL. The full-span model made use of steady flap blowing and a lifting centerbody to achieve high lift coefficients. The test occurred during April through June of 2007 and included objectives for advancing the state-of-the-art of powered lift testing through gathering force and moment data, on-body pressure data, and off-body flow field measurements during automatically controlled blowing conditions. Data were obtained for variations in model configuration, angles of attack and sideslip, blowing coefficient, and height above ground. The database produced by this effort is being used to advance design techniques and computational tools for developing systems with integrated powered lift technologies.

Type
Research Article
Information
The Aeronautical Journal , Volume 113 , Issue 1140: The International Powered Lift Conference 2008: A Special issue , February 2009 , pp. 129 - 137
Copyright
Copyright © Royal Aeronautical Society 2009 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Kudirka, J. ET AL. A-6A circulation control wing flight test final report, 13 April 1979.Google Scholar
2. Sellers, W.L. III, Jones, G.S. and Moore, M.D., Flow control research at NASA Langley in support of high-lift augmentation, AIAA-2002-6006.Google Scholar
3. Northrop, J. K, The development of all-wing aircraft, May 1947, 35th Wilbur Wright Memorial Lecture.Google Scholar
4. Bell, J.H., Schairer, E.T., Hand, L.A. and Mehta, R.D., Surface pressure measurements using luminescent coatings, Annual Rev Fluid Mech, 2001, 33, pp 155–206.Google Scholar
5. Liu, T. and Sullivan, J.P., Pressure and temperature sensitive paints, Experimental Fluid Dynamics, 2004, Berlin, Springer-Verlag.Google Scholar
6. Lakowicz, J., Principles of Fluorescence Spectroscopy, 1999, Second Edition, pp 239–242, Kluwer Academic/Plenum Publishers, New York.Google Scholar
7. Johansen, E.S., Rediniotis, O.K. and Jones, G.S., The compressible calibration of miniature multi-hole probes, J Fluids Eng, 2001, 123, (3), pp 128–138.Google Scholar
8. Rediniotis, O.K., Hoang, N.T. and Telionis, D.P., The seven-hole probe: its calibration and use, 1993, Forum on Instructional Fluid Dynamics Experiments, 152, pp 21–26.Google Scholar
9. Lin, J.C., Jones, G.S., Allan, B.G., Westra, B.K., Collins, S.W. and Zeune, C.H., Flow-field measurement of a hybrid wing body model with blown flaps, AIAA-2008-6718.Google Scholar