A Caltech Library Service

Boundary Layer Temperature Recovery Factor on a Cone at Nominal Mach Number Six


Mackay, Douglas Severance (1953) Boundary Layer Temperature Recovery Factor on a Cone at Nominal Mach Number Six. Engineer's thesis, California Institute of Technology. doi:10.7907/8DEC-WE68.


NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. An investigation was conducted to determine the temperature recovery factors for laminar boundary layer on a cone at free stream Mach numbers from 5.6 to 5.9. The investigation was conducted in the GALCIT 5" x 5? continuous-flow, closed-circuit wind tunnel (Leg No. 1). Two twenty degree cone models about three inches in length were used. One model was composed of a ceramic core with a thin (0.010? to 0.015?) steel surface, and the second was a hollow copper shell of 0.005? thickness. One-phase and two-phase (condensation) flow conditions were investigated. Temperature recovery factors were determined from the data obtained from the tests conducted with one-phase airflows. The ratios of the temperatures recovered on the cone surface to the respective stagnation temperatures were computed from the data obtained in the two-phase airflow investigations and were compared with these ratios for the one-phase airflows. The local temperature recovery factors for the laminar boundary layer were determined to be 0.844 ? 0.008 for Reynolds numbers from 2.1 x 10[superscript 4] to 5.4 x 10[superscript 5] . For this range of Reynolds numbers the recovery factor was found to be independent of the Reynolds number. The independence of the recovery factor on the Mach number was substantiated (by comparison with results of previous investigations at lower Mach numbers) for Mach numbers up to 5.9. The ratios of the temperature recovered on the cone to the stagnation temperature were found to be the same for one and two-phase airflows. The square root of the Prandtl number evaluated at the mean of the temperatures of the cone surface for the various flow conditions investigated was found to be less than one per cent lower than the mean of the experimental temperature recovery factors. The results of this investigation are in agreement with those of previous investigations at lower Mach numbers and, within the limits of experimental accuracy, verify theoretical solutions.

Item Type:Thesis (Engineer's thesis)
Subject Keywords:Aeronautical Engineering
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Nagamatsu, Henry T.
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1953
Record Number:CaltechETD:etd-05122003-095635
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:1729
Deposited By: Imported from ETD-db
Deposited On:13 May 2003
Last Modified:25 May 2023 18:30

Thesis Files

PDF (Mackay_ds_1953.pdf) - Final Version
See Usage Policy.


Repository Staff Only: item control page