NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
Resistance of a delta wing in a supersonic flowThe resistance of a delta wing at small angle of attack in supersonic conical flow with its leading edges within the Mach cone is calculated by a method that separates out the suction force.
Document ID
19930093957
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Karpovich, E A
Frankl, F I
Date Acquired
August 16, 2013
Publication Date
April 1, 1951
Report/Patent Number
NACA-TM-1283
Report Number: NACA-TM-1283
Accession Number
93R23283
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
DRAG - WINGS, DELTA
THEORIES - WINGS, SUPERSONIC

Related Records

There are no records associated with this record.
No Preview Available