A Caltech Library Service

An Experimental Investigation of Hypersonic Flow over Blunt-Nosed Bodies at a Mach Number 5.8


Fraasa, Donald Gordon (1957) An Experimental Investigation of Hypersonic Flow over Blunt-Nosed Bodies at a Mach Number 5.8. Engineer's thesis, California Institute of Technology. doi:10.7907/G6D1-N841.


NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. An experimental investigation to obtain schlieren photographs of the flow over several blunt-nosed bodies and to determine the surface static pressure distribution on certain of these models was conducted in the GALCIT hypersonic wind tunnel, leg no. 1, at a nominal Mach number of 5.8 and a free stream Reynolds number per inch of 2.22 x 10[...]. Schlieren photographs were made of the following blunt-nosed models, all with cylindrical afterbodies, at angles of yaw of 0, 4, and 8 degrees: a family of nine round-nosed bodies with nose radii of curvature varying from the radius of the afterbody cylinder (hemispherical nose) to infinity (flat nose), two concave-nosed bodies having nose radii of curvature equal to 0.8 and 1.6 times the afterbody diameter, and three flat-nosed cylinders with rounded shoulders whose radii of curvature were .083, .125, and .208 times the afterbody diameter. Static pressure distributions at angles of yaw of 0, 4, and 8 degrees were determined for three of the blunt bodies: (1) the flatnosed cylinder with infinite nose radius of curvature, (2) the flatnosed cylinder with a rounded shoulder of radius equal to .208 of the afterbody diameter, and (3) a round-nosed cylinder with nose radius of curvature equal to 1.3 times the afterbody diameter. The schlieren photographs were analyzed on a contour projector to measure shock standoff distances, to determine the sonic point on the shock, and to observe shock shape. Data derived from these studies and the pressure distributions are presented in graphical form. Comparisons are made between the experimental results and appropriate theoretical approximations for hypersonic flow.

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):
  • Lees, Lester
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1957
Record Number:CaltechETD:etd-07082004-144120
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:2833
Deposited By: Imported from ETD-db
Deposited On:13 Jul 2004
Last Modified:09 Oct 2023 22:06

Thesis Files

PDF (Fraasa_dc_1957.pdf) - Final Version
See Usage Policy.


Repository Staff Only: item control page