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Experimental Investigation of a Point Design Optimized Arrow Wing HSCT ConfigurationThe M2.4-7A Arrow Wing HSCT configuration was optimized for straight and level cruise at a Mach number of 2.4 and a lift coefficient of 0.10. A quasi-Newton optimization scheme maximized the lift-to-drag ratio (by minimizing drag-to-lift) using Euler solutions from FL067 to estimate the lift and drag forces. A 1.675% wind-tunnel model of the Opt5 HSCT configuration was built to validate the design methodology. Experimental data gathered at the NASA Langley Unitary Plan Wind Tunnel (UPWT) section #2 facility verified CFL3D Euler and Navier-Stokes predictions of the Opt5 performance at the design point. In turn, CFL3D confirmed the improvement in the lift-to-drag ratio obtained during the optimization, thus validating the design procedure. A data base at off-design conditions was obtained during three wind-tunnel tests. The entry into NASA Langley UPWT section #2 obtained data at a free stream Mach number, M(sub infinity), of 2.55 as well as the design Mach number, M(sub infinity)=2.4. Data from a Mach number range of 1.8 to 2.4 was taken at UPWT section #1. Transonic and low supersonic Mach numbers, M(sub infinity)=0.6 to 1.2, was gathered at the NASA Langley 16 ft. Transonic Wind Tunnel (TWT). In addition to good agreement between CFD and experimental data, highlights from the wind-tunnel tests include a trip dot study suggesting a linear relationship between trip dot drag and Mach number, an aeroelastic study that measured the outboard wing deflection and twist, and a flap scheduling study that identifies the possibility of only one leading-edge and trailing-edge flap setting for transonic cruise and another for low supersonic acceleration.
Document ID
20000044869
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Narducci, Robert P.
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Sundaram, P.
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Agrawal, Shreekant
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Cheung, S.
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Arslan, A. E.
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Martin, G. L.
(McDonnell-Douglas Aerospace Long Beach, CA United States)
Date Acquired
August 19, 2013
Publication Date
December 1, 1999
Publication Information
Publication: First NASA/Industry High-Speed Research Configuration Aerodynamics Workshop
Issue: Part 3
Subject Category
Aircraft Design, Testing And Performance
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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