Flow Characteristics of A 12-In. Intermittent Supersonic Tunnel

Item

Title
Flow Characteristics of A 12-In. Intermittent Supersonic Tunnel
Date
1963
Index Abstract
Not Available
Photo Quality
Incomplete
Report Number
AEDC TDR 63-203
Creator
Anderson, A.
Corporate Author
ARO, Inc.
Extent
37
Identifier
AD0418578
Distribution Classification
1
Contract
AF 40(600)-1000
DoD Project
None Given
DoD Task
None Given
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Abstract
A compilation has been made of all calibration data obtained since 1958 in the von Karman Gas Dynamics Facility's 12-Inch Supersonic Tunnel (D). Test section flow characteristics are pre sented for the nominal Mach number range from 1.5 to 5 over the available Reynolds number range. Along the axis of the test section for all con tours the maximum variation in Mach number is within =0.01, and the average flow angles in pitch and yaw are less than 0.2 deg. Somewhat larger variations in Mach number and flow angu larity are found off-axis. At the higher Mach numbers, significant changes in the average test section Mach number with decreasing Reynolds number are accompanied by corresponding changes in the tunnel boundary layer.
Report Availability
Full text available by request
Date Issued
1963-09
Publisher
Arnold Air Force Station, TN : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force
Provenance
IIT
Type
report
Format
37 pages ; 28 cm.