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The aerodynamic design of the oblique flying wing supersonic transportThe aerodynamic design of a supersonic oblique flying wing is strongly influenced by the requirement that passengers must be accommodated inside the wing. It was revealed that thick oblique wings of very high sweep angle can be efficient at supersonic speeds when transonic normal Mach numbers are allowed on the upper surface of the wing. The goals were motivated by the ability to design a maximum thickness, minimum size oblique flying wing. A 2-D Navier-Stokes solver was used to design airfoils up to 16 percent thickness with specified lift, drag and pitching moment. A new method was developed to calculate the required pressure distribution on the wing based on the airfoil loading, normal Mach number distribution and theoretical knowledge of the minimum drag of oblique configurations at supersonic speeds. The wing mean surface for this pressure distribution was calculated using an inverse potential flow solver. The lift to drag ratio of this wing was significantly higher than that of a comparable delta wing for cruise speeds up to Mach 2.
Document ID
19900019224
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Vandervelden, Alexander J. M.
(Stanford Univ. CA, United States)
Kroo, Ilan
(Stanford Univ. CA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1990
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-CR-177552
A-90168
NAS 1.26:177552
Accession Number
90N28540
Funding Number(s)
CONTRACT_GRANT: NCA2-343
PROJECT: RTOP 505-60-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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