THE LAMINAR BOUNDARY LAYER ON A CONE IN A SUPERSONIC AIR STREAM AT ZERO ANGLE OF ATTACK

reportActive / Technical Report | Accession Number: AD0604783 | Open PDF

Abstract:

This report demonstrates that the integration of the equations for the laminar boundary layer on a cone in a supersonic air stream can be reduced to the equations for the flat plate. The simple result is obtained, that on the cone the boundary layer is different by 1square root of 3 as compared to the plate. The mean friction coefficient and the heat transfer coefficient are greater by the factor 23 times the square root of 3.

Author(s):
Hantzsche, W. ; Wendt, H.
Author Organization(s):
RAND CORP SANTA MONICA CA
Supplementary Note:
Trans. of mono. die Laminare Grenzschicht bei einem mit Uberschallgeschwindigkeit Angestromtem Nichtangestellten Kreiskegel, n.p., n.d.
Pagination:
0009

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release, Document Partially Illegible
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited. Document Partially Illegible.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
T-6, TT-64-71277
Monitor Series:
USAF
 Subject Terms
Communities of Interest:
Air Platforms
Descriptor(s):
*CONICAL BODIES, *LAMINAR BOUNDARY LAYER, *SUPERSONIC FLOW, ANGLE OF ATTACK, DIFFERENTIAL EQUATIONS, FLAT PLATE MODELS, FRICTION, HEAT TRANSFER COEFFICIENTS, NUMERICAL INTEGRATION, PRESSURE, SHOCK WAVES
Field(s)/Group(s):
Numerical Mathematics
Keyword(s):
RAND PROJECT
Report Date:
1947 Nov 13