Email RIS file
Bookmark
Report an Issue

Reynolds Number, Compressibility, and Leading-Edge Bluntness Effects on Delta-Wing Aerodynamics

Author:
Luckring, James M.
Published:
[2004].
Physical Description:
1 electronic document
Online Version

Availability

I Want It
I Want It

Finding items...

Restrictions on Access:
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary:
An overview of Reynolds number, compressibility, and leading edge bluntness effects is presented for a 65 degree delta wing. The results of this study address both attached and vortex-flow aerodynamics and are based upon a unique data set obtained in the NASA-Langley National Transonic Facility (NTF) for i) Reynolds numbers ranging from conventional wind-tunnel to flight values, ii) Mach numbers ranging from subsonic to transonic speeds, and iii) leading-edge bluntness values that span practical slender wing applications. The data were obtained so as to isolate the subject effects and they present many challenges for Computational Fluid Dynamics (CFD) studies.
Other Subject(s):
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 20040110336.
24th International Congress of the Aeronautical Sciences; 2004; Unknown.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15964844