Supersonic Laminar Boundary Layer Flow Past a Wavy Wall with Multiple Separation Regions.

Abstract

Laminar flow over wave shaped walls with multiple separation bubbles were studied using an implicit finite difference technique. Solutions are presented for Mach 3 and 6, Re 100 000 and 200 000, Tw/To = 0.45, and 0.675 and protuberance height to width ratio from 0 to 0.1. Results are compared with empirical correlations and experimental data.

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1975
Accession Number
ADA007433

Entities

People

  • A. Polak
  • M. J. Werle
  • S. D. Bertke
  • V. N. Vatsa

Organizations

  • University of Cincinnati

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Experimental Data
  • Flow
  • Laminar Boundary Layer
  • Laminar Flow
  • Layers

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers