Accession Number : AD0259888

Title :   DETERMINATION OF TEST-SECTION, AFTER-SHOCK, AND STAGNATION CONDITIONS IN HOTSHOT TUNNELS USING REAL NITROGEN AT TEMPERATURES FROM 3000 TO 4000 K

Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN

Personal Author(s) : GRABAU,MARTIN ; HUMPHREY,RICHARD L. ; LITTLE,WANDA J.

Report Date : JUL 1961

Pagination or Media Count : 1

Abstract : A new method is set forth for computation of test-section, after-shock, and stagnation conditions in hotshot tunnels of Arnold Center, using nitrogen at stagnation temperatures from 3000 to 4000 K. The basic data are the pressure600)800) Unclassified report DESCRIPTORS: *Hypersonic wind tunnels, Gas flow, Mathematical analysis, Nitrogen, Pres sure Temperature, *Thermodynamics, Aerodynam ics, *Hypersonics. A new method is set forth for computation of test-section, after-shock, and stagnation conditions in hotshot tunnels of Arnold Center, using nitrogen at stagnation temperatures from 3000 to 4000 K. The basic data are the pressure and temperature of the gas in the arc chamber prior to firing the arc, the pressure in the arc chamber after firing the arc, and the pitot pressure in t e test section. The latter 2 quantities are functions of time. Whenever possible, advantage is taken of perfect gas relationships. Allowance is made for the time of transit of a pressure signal between the throat and the test section. (Author)

Descriptors :   *HYPERSONIC CHARACTERISTICS, *HYPERSONIC WIND TUNNELS, *THERMODYNAMICS, AERODYNAMIC CHARACTERISTICS, GAS FLOW, MATHEMATICAL ANALYSIS, NITROGEN, PRESSURE, TEMPERATURE

Distribution Statement : APPROVED FOR PUBLIC RELEASE