THEORETICAL DETERMINATION OF THE DISCHARGE COEFFICIENTS OF AXISYMMETRIC NOZZLES UNDER CRITICAL FLOWS,

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Abstract:

Discharge coefficients of axisymmetric contoured nozzles under steady, critical flow conditions were studied theoretically. In the analysis, axisymmetric compressible laminar boundary layer flow was considered for a perfect gas with Prandtl number unity and viscosity proportional to temperature. The wall was assumed to be adiabatic. Solutions to the equations describing the discharge coefficient were obtained analytically in closed form when the pressure-gradient parameter Beta was infinite. Numerical computations were carried out for two other cases, Beta 2 and Beta 1. Author

Author(s):
Tang, S. P.
Author Organization(s):
PURDUE UNIV LAFAYETTE IND PROJECT SQUID HEADQUARTERS
Supplementary Note:
Prepared in cooperation with Princeton Univ., N. J.
Pagination:
0042

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
SQUID-TR-PR-118-PU
Contract/Grant Number(s):
N00014-67-A-0226-0005
Project Number(s):
NR-098-038
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
(*NOZZLE GAS FLOW, AXIALLY SYMMETRIC FLOW), SUPERSONIC NOZZLES, COMPRESSIBLE FLOW, LAMINAR BOUNDARY LAYER, ADIABATIC GAS FLOW, NUMERICAL ANALYSIS, NOZZLE THROATS, THEORY
Field(s)/Group(s):
Aerodynamics, Fluid Mechanics
Keyword(s):
CRITICAL FLOW, SQUID PROJECT
Report Date:
1969 Oct 01