THERMAL EFFECTS OF SHOCKWAVE TURBULENT BOUNDARY LAYER INTERACTION AT MACH NUMBERS 3 AND 5

reportActive / Technical Report | Accession Number: AD0298671 | Open PDF

Abstract:

No Abstract Identified

Author(s):
Levin, V. ; Fabish, T. J.
Author Organization(s):
NORTH AMERICAN AVIATION INC COLUMBUS OH
Supplementary Note:
DOI: 10.21236/AD0298671
Pagination:
0185

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):
NA-62H-795
Contract/Grant Number(s):
NOW-61-0679
Monitor Series:
NAVWEPS
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_1.2.7_Experimentation; JCA_5_Command and Control; JCA_5.3_Planning; JCA_1_Force Support; JCA_1.2.6_Concepts; JCA_1.2_Force Preparation; JCA_JCA_4.1.2_Sustain the Force; JCA_4.1_Deployment and Distribution; JCA_6.4.1_Secure Information Exchange
Modernization Areas:
Hypersonics
Communities of Interest:
Weapons Technologies
Descriptor(s):
*TURBULENT BOUNDARY LAYER, *FLAT PLATE MODELS, HEAT TRANSFER, PRESSURE, AIR EJECTORS, SHOCK TUBES, SUPERSONIC CHARACTERISTICS, LOAD DISTRIBUTION
Field(s)/Group(s):
Fluid Mechanics
Report Date:
1962 Nov 12