Highly cooled boundary layer transition data in a shock tube
Abstract
Tests were conducted in a shock tube sidewall boundary layer to obtain data on transition Reynolds number for a unit Reynolds number and shock Mach number range between 0.5 x 10 to the 6th and 4 x 10 to the 6th Re/ft and Mach number between 3 and 15, respectively. At a fixed unit Reynolds number of about 0.5 x 10 to the 6th per foot a multiple transition reversal curve was obtained for the cooling range investigated. In the intermediate range of wall cooling, measured transition Reynolds numbers were approximately four times greater than reported in previous investigations. Data obtained using microphones show that at a fixed shock Mach number, transition Reynolds number increases with decreasing acoustic fluctuations but is unit Reynolds number dependent.
 Publication:

Modern Developments in Shock Tube Research
 Pub Date:
 1975
 Bibcode:
 1975mdst.symp..127B
 Keywords:

 Boundary Layer Transition;
 Cooling;
 Shock Tubes;
 Transition Temperature;
 Wall Temperature;
 Acoustic Instability;
 Data Acquisition;
 Mach Number;
 Pressure Effects;
 Reynolds Number;
 Shock Wave Propagation;
 Test Facilities;
 Time Dependence;
 Transition Flow;
 Fluid Mechanics and Heat Transfer