APPROXIMATE SOLUTIONS FOR AERODYNAMIC HEATING OF REENTRY VEHICLES

Abstract

Aerodynamic heating of space vehicles during reentry with constant aerodynamic coefficients is considered. General relations for the conditions at the maximum heating rate, and for the total heat input at the stagnation point from entry to any point in the trajectory, are developed. The relations are not subject to the restrictions of skip or exit trajectories with entry velocity greater than the circular speed. The relation presented for the heat input has 2 parts. The first, which is the most significant part of the heat input, is of closed form. The second part is left in terms of an integral and evaluated by Simpson's rule. Only a small number of steps are required in the numerical evaluation of this integral, thus making this solution much shorter than direct numerical integration. The numerical results calculated from this solution show good agreement with those from the direct numerical integration. (Author)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1961
Accession Number
AD0268826

Entities

People

  • Charles J. Ruger

Organizations

  • New York University Tandon School of Engineering

Tags

DTIC Thesaurus Topics

  • Aerodynamic Heating
  • Agreements
  • Coefficients
  • Descent Trajectories
  • Heat Energy
  • Heating
  • Integrals
  • Numerical Integration
  • Orbits
  • Reentry Vehicles
  • Spacecraft
  • Stagnation Point
  • Test And Evaluation
  • Trajectories
  • Vehicles

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Dynamics.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris