Accession Number:

AD0609593

Title:

CALIBRATION OF A PLASMA JET FACILITY FOR SIMULATION OF BALLISTIC MISSILE RE-ENTRY,

Descriptive Note:

Corporate Author:

AVCO CORP WILMINGTON MASS RESEARCH AND ADVANCED DEVELOPMENT DIV

Personal Author(s):

Report Date:

1959-02-20

Pagination or Media Count:

42.0

Abstract:

A procedure has been developed for determining the stagnation enthalpy, static enthalpy, stagnation pressure, velocity, and Mach number of a subsonic air plasma jet. The determination is based upon measurements of airflow, power input, and energy losses, and employs the equation of state and an approximate compressible flow equation for dissociated air. The steady state heat transfer rate from the plasma jet to the stagnation region of a large plate has been measured using constant-flow water calorimeters. The range of aerothermodynamic conditions covered in the experiments was as follows stagnation enthalpy from 3500 to 12,000 Btulb, stagnation pressure from 1 to 1.7 atm, stagnation-point velocity gradient from 30,000 to 100,000 sec-1. These conditions simulate flow over the nose regions of high-performance re-entry vehicles for flight velocities between 13,000 and 24,000 ftsec at altitudes in the neighborhood of 130,000 ft. The observed heat transfer rates ranged from 800 to 1500 Btusquare ft sec. These observed heat flux values were found to agree approximately with a heat transfer correlation for hypersonic flow based upon shock tube experiments. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE