Accession Number : AD0451306


Title :   AN EXPERIMENTAL INVESTIGATION IN A MODEL TUNNEL TO DETERMINE THE STARTING AND RUNNING PRESSURE RATIO REQUIREMENTS OF THE PWT 16-FOOT SUPERSONIC TUNNEL AT M = 3.5 TO 6.0


Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN


Personal Author(s) : Jackson, F M ; Blanchard, P F


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/451306.pdf


Report Date : Nov 1964


Pagination or Media Count : 46


Abstract : A determination of the minimum pressure ratios required for starting and running in the PWT, Supersonic (16S) was required in the Mach number range from 3.5 to 6.0 because of the work now in progress to extend the Mach number range of that facility. Estimates of these requirements were determined by tests in the AWT, Supersonic (1S) model tunnel. For these tests the variable geometry diffuser contained a closed-off scoop, and a model was installed in the test section. The results of these tests indicate that for Tunnel 16S the minimum starting pressure ratio requirements vary from 58 percent normal shock recovery at M = 3.50 to 45 percent at M = 5.85. The minimum running requirements vary from 112 normal shock recovery at M = 3.50 to 85 percent at M = 5.85.


Descriptors :   *HYPERSONIC WIND TUNNELS , *SUPERSONIC WIND TUNNELS , DIFFUSERS , EXPERIMENTAL DATA , INSTALLATION , MILITARY REQUIREMENTS , MODEL TESTS , OPERATION , PERFORMANCE(ENGINEERING) , PRESSURE , STARTING , SUPERSONIC DIFFUSERS , TEST METHODS , WIND TUNNEL MODELS


Subject Categories : Test Facilities, Equipment and Methods


Distribution Statement : APPROVED FOR PUBLIC RELEASE