EFFECTS OF UNIT REYNOLDS NUMBER, NOSE BLUNTNESS, AND ROUGHNESS ON BOUNDARY LAYER TRANSITION

reportActive / Technical Report | Accession Number: AD0262482 | Open PDF

Abstract:

This analysis consists of two parts. A technique is presented for measuring heat transfer rates on a model and for fixing the temperature distribution at a given value. The technique is applied to the particular case of turbulent heat transfer on a blunt body at a Mach number of 3.98.

Author(s):
Potter, J. L. ; Whitfield, Jack D.
Author Organization(s):
ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)
Pagination:
0084

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
256
Monitor Series:
NATO
 Subject Terms
Joint Capability Areas:
JCA_3_Force Application; JCA_5.3_Planning; JCA_5_Command and Control; JCA_3.1.1_Maneuver to Engage; JCA_3.1_Maneuver; JCA_1.2.7_Experimentation; JCA_1_Force Support; JCA_1.2_Force Preparation; JCA_3.2_Engagement; JCA_3.2.1_Kinetic Means; JCA_6_Net Centric; JCA_6.4.1_Secure Information Exchange; JCA_4.5.4_Requirements Definition; JCA_4.5_Operational Contract Support
Communities of Interest:
Air Platforms
Descriptor(s):
*BLUNT BODIES, *BOUNDARY LAYER, *REYNOLDS NUMBER, *WIND TUNNEL MODELS, LAMINAR BOUNDARY LAYER, MACH NUMBER, MODEL TESTS, SUPERSONIC FLOW, TURBULENCE
Field(s)/Group(s):
Fluid Mechanics
Report Date:
1960 Apr 01