NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Due to the lapse in federal government funding, NASA is not updating this website. We sincerely regret this inconvenience.

Back to Results
Cones in Supersonic FlowIn the case of cones in axially symmetric flow of supersonic velocity, adiabatic compression takes place between shock wave and surface of the cone. Interpolation curves betwen shock polars and the surface are therefore necessary for the complete understanding of this type of flow. They are given in the present report by graphical-numerical integration of the differential equation for all cone angles and airspeeds.
Document ID
20030067375
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Hantzsche, W. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Wendt, H. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 21, 2013
Publication Date
August 1, 1947
Publication Information
Publication: Jahrbuch 1942 der deutschen Luftfahrtforschung
Subject Category
Aerodynamics
Report/Patent Number
NACA-TM-1157
Report Number: NACA-TM-1157
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

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