CaltechAUTHORS
  A Caltech Library Service

End-Wall Heat-Transfer Effects on the Trajectory of a Reflected Shock Wave

Sturtevant, Bradford and Slachmuylders, Erik (1964) End-Wall Heat-Transfer Effects on the Trajectory of a Reflected Shock Wave. Physics of Fluids, 7 (8). pp. 1201-1207. ISSN 0031-9171. http://resolver.caltech.edu/CaltechAUTHORS:STUpof64

[img]
Preview
PDF - Published Version
See Usage Policy.

604Kb

Use this Persistent URL to link to this item: http://resolver.caltech.edu/CaltechAUTHORS:STUpof64

Abstract

The trajectory of a reflected shock wave has been measured near the end wall where the motion is perturbed by the displacement effect of heat transfer to the wall. In this experiment an x, t diagram of the reflection of an Ms = 4.08 shock wave was constructed by measuring shock arrival times with small probes. The parameter that measures the (negative) displacement thickness of the end-wall thermal layer, a ``Reynolds number'' R based on the shock velocity, the time after reflection, and the thermal diffusivity was varied between 9 and 600. In this range the measured deviation of the shock trajectory from ideal varied from 1½ to 17 shock thicknesses. The shock velocity was determined by differentiating a least-squares fit of the data to a fourth-order polynomial in R–½. In the range of the experiments the shock accelerated from a velocity that was 20% below ideal to one that was within 4% of ideal. Experiment agrees with boundary-layer theory above R = 150 for the shock trajectory and above R = 25 for the shock velocity, and implies that the exponent of the power-law dependence of the thermal conductivity on temperature is 0.81 ± 0.02. The small deviation of the shock velocity from boundary-layer theory predicted for R < 100 by higher-order theory is not observed, though since this theory falls just within the estimated experimental error this result is somewhat qualified. In any case, the unexpected agreement with first-order theory at small R indicates that molecular effects, such as temperature jump, do not play a large role when the shock is more than ten shock thicknesses from the end wall.


Item Type:Article
Related URLs:
URLURL TypeDescription
http://dx.doi.org/10.1063/1.1711362DOIUNSPECIFIED
Additional Information:© 1964 The American Institute of Physics. Received 30 October 1963. This work was supported by the National Aeronautics and Space Administration under Grant NaG-40-60.
Funders:
Funding AgencyGrant Number
NASANaG-40-60
Record Number:CaltechAUTHORS:STUpof64
Persistent URL:http://resolver.caltech.edu/CaltechAUTHORS:STUpof64
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:12158
Collection:CaltechAUTHORS
Deposited By: Archive Administrator
Deposited On:27 Oct 2008 22:30
Last Modified:26 Dec 2012 10:27

Repository Staff Only: item control page