NORMAL SHOCK WAVE CALCULATIONS IN AIR AT FLIGHT SPEEDS UP TO 25,000 FT./SEC,

Abstract

New calculations of the equilibrium gas proper ties behind a normal shock wave are presented based on the 1959 ARDC Model Atmosphere. Graphs of pressure, density, and temperat8re are pre sented for conditions behind a normal shock wave and at the stagnation point following an isen tropic compression, for high altitude hypersonic flight. The regime treated covers altitude from 100,000 feet to 400,000 feet in increments of 2000 feet, and a range of flight speeds from 10,000 to 25,000 feet per second. (Author)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1962
Accession Number
AD0415921

Entities

People

  • C.a. Cook
  • L.m. Gilbert
  • S.m. Scala

Organizations

  • General Electric

Tags

DTIC Thesaurus Topics

  • Altitude
  • Atmospheres
  • Compression
  • Flight
  • Flight Speeds
  • High Altitude
  • Hypersonic Flight
  • Shock
  • Shock Waves
  • Stagnation Point
  • Waves

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Fluid Dynamics.
  • Spectroscopy.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow