Experimental Heat Transfer to Blunt Axisymmetric Bodies Near the Limit of Continuum Flow

Item

Title
Experimental Heat Transfer to Blunt Axisymmetric Bodies Near the Limit of Continuum Flow
Date
1962
Index Abstract
Coming Soon
Photo Quality
Not Needed
Report Number
AEDC TDR 62-155
Creator
Potter, J. Leith
Miller, John T.
Corporate Author
ARO, Inc.
Laboratory
Arnold Engineering Development Center
Extent
20
Identifier
AD0281911
Access Rights
ASTIA
Distribution Classification
1
Contract
AF 40(600)-1000
DoD Project
8953
DoD Task
895306
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Abstract
Measurements of average heat-transfer rates to blunt-nosed, axisymmetric, cold-walled bodies in a low-density, hypervelocity wind tunnel are given. Stream density was such that Reynolds and Knudsen numbers, based on nose radius and conditions immediately behind the bow shock, varied from 5 to 20 and 0.11 to 0.056, respectively. Thus, scaling on the basis of Knudsen number, these conditions may be said to simulate a body of one-foot nose radius at as much as 315,500-ft altitude. Heat-transfer rates are discussed in relation to the flow model successfully used in the past for studies of flows of high Reynolds number. In this context, it was found that measured heat-transfer rates to hemispheres below shock-layer Reynolds numbers of 20 exhibited a decreasing nondimensionalized rate relative to that estimated by methods appropriate to high Reynolds number conditions. This behavior is in accord with various applicable theories. Rates for the flat-faced bodies showed no tendency to decrease, and they were somewhat higher than predicted by theories for high Reynolds numbers.
Report Availability
Full text available
Date Issued
1962-08
Publisher
Arnold Air Force Station, TN : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force
Provenance
IIT
Type
report
Format
1 online resource
Media
AEDCTDR62-155.pdf