Boundary Layer Separation in 2 and 3 Dimensional High Speed Blow.

reportActive / Technical Report | Accession Number: ADA181301 | Open PDF

Abstract:

Laminar boundary flow on cones in supersonic flow was calculated using a modified Method of Integrals to account for the change in velocity profiles in the separated regions. The work was extended to three dimensions and compared to experimental data. Significant progress was made in the modeling of th flows and in particular the regions of separated and reverse flow in the boundary layer.

Author(s):
Holt, Maurice
Author Organization(s):
CALIFORNIA UNIV BERKELEY COLL OF ENGINEERING
Descriptive Note:
Final rept. May 83-Apr 84,
Pagination:
0011

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AFOSR-TR-87-0696
Contract/Grant Number(s):
AFOSR-83-0199
Task Number(s):
A1
Project Number(s):
2307
Monitor Series:
TR-87-0696
 Subject Terms
Joint Capability Areas:
JCA_1.2.3_Educating; JCA_1.2.7_Experimentation; JCA_4.6_Engineering
Communities of Interest:
Air Platforms
Descriptor(s):
*SECONDARY FLOW, *SUPERSONIC FLOW, *FLOW SEPARATION, *BOUNDARY LAYER FLOW, BOUNDARY LAYER, INTEGRALS, LAMINAR BOUNDARY LAYER, LAMINAR FLOW, PROFILES, SEPARATION, VELOCITY, THREE DIMENSIONAL FLOW, TWO DIMENSIONAL FLOW, HIGH ANGLES, ANGLE OF ATTACK, CONICAL BODIES
Field(s)/Group(s):
Fluid Mechanics
Keyword(s):
Reverse flow, WUAFOSR2307A1, PE61102F
Report Date:
1987 May 01