EXACT SIMILAR SOLUTIONS OF THE LAMINAR BOUNDARY-LAYER EQUATIONS

Abstract

Tables are given of 1400 values that may be used to determine skin friction, heat transfer, and appropriate boundary-layer thickness parameters for reentry vehicles. Assuming a perfect homogeneous gas atmosphere, the values were computed to an accuracy of four significant figures in terms of eight parameters: positive pressure gradient, Mach number, temperature-viscosity law, leading-edge sweep, wall temperature, Prandtl number, local streamwise velocity, and mass transfer at the surface (positive only). The accuracy requirements were relaxed for very high accelerations. More than five-sixths of the values are presented for the first time; the rest were recomputed to the accuracy of the present program. A key to the tables displays graphically the solutions available. Numerical procedures are given in detail. For application to cases in which not all of the eight parameters are similar, the direct effects of the nonsimilar terms may be calculated by asymptotically expanding the full boundary-layer equations in terms of the departures from similarity.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1967
Accession Number
AD0665969

Entities

People

  • C. F. Dewey Jr.
  • Joseph F. Gross

Organizations

  • RAND Corporation

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Equations
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Heat Transfer Coefficients
  • Laminar Boundary Layer
  • Mach Number
  • Mass Transfer
  • Mechanical Properties
  • Prandtl Number
  • Pressure Gradients
  • Skin Friction

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Regression Analysis.