A Caltech Library Service

Numerical simulation of viscous reacting hypersonic flow past cones


Shariff, Shaun (1999) Numerical simulation of viscous reacting hypersonic flow past cones. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/D6TR-5Z18.


NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. The stepback and partial grid techniques were used in the numerical simulation of laminar viscous reacting flows past cones at incidence. The stepback technique is a method for computing exactly flows which are truly conical, and can be an effective approximate method for nearly conical flows such as viscous flow past cones. The partial grid technique uses a stepback solution as the upstream boundary condition for a time-marching calculation, and is more accurate than the stepback method. Both frozen and chemically active equilibrium flow were considered, using the Ideal Dissociating Gas model. Computations were performed for frozen hypersonic flow past a 10[...] half-angle cone inclined at 24[...] incidence, and for hypervelocity flow past a 15[...] half-angle cone at 30[...] incidence with active dissociation and recombination chemistry. These computations were compared with experiments, and the effects of equilibrium and non-equilibrium chemistry were observed. These calculations also show that the effects of chemistry on heat transfer and separation location are small and of the same order as the errors associated with the stepback method. Therefore, for high accuracy in computing reacting flows, the partial grid method should be used.

Item Type:Thesis (Dissertation (Ph.D.))
Subject Keywords:aeronautics ; hypersonic flow
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Pullin, Dale Ian
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 October 1998
Funding AgencyGrant Number
Office of Naval ResearchN-00014-90-J-1778
Air Force Office of Scientific ResearchF49620-93-1-0338
Record Number:CaltechETD:etd-02212008-155520
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:707
Deposited By: Imported from ETD-db
Deposited On:11 Mar 2008
Last Modified:21 Dec 2019 01:39

Thesis Files

PDF (Shariff_s_1999.pdf) - Final Version
See Usage Policy.


Repository Staff Only: item control page