Computer program accounts for effective nozzle geometry changes due to boundary layer displacement thickness. Program input and output are discussed

Goldman, L. J.

Vanco, M. R.

English

NASA Technical Reports Server

October 1972
	
CORRECTED COPY	 B72-10070 
NASA TECH BRIEF 
Lewis Research Center 
NASA Tech Briefs announce new technology derived from the U.S. space program. They are issued to encourage 
commercial application. Tech Briefs are available on a subscription basis from the National Technical Information 
Service, Springfield, Virginia 22151. Requests for individual copies or questions relating to the Tech Brief program may 
be directed to the Technology Utilization Office, NASA, Code KT, Washington, D.C. 20546. 
Design of Two-Dimensional Sharp-Edged-Throat Supersonic Nozzle 
with Boundary-Layer Correction 
The problem: 
Available computer programs that were written for 
the design of sharp-edged-throat supersonic nozzles did 
not account for effective nozzle geometry changes due 
to boundary-layer displacement thickness. 
The solution: 
A computer program has been developed for the 
design of sharp-edged-throat supersonic nozzles where 
losses are accounted for by correcting the ideal nozzle 
geometry for boundary-layer displacement thickness. 
How it's done: 
The ideal nozzle is designed by the method of charac-
teristics. Boundary-layer parameters are calculated by 
Cohen and Reshotko's method for laminar flow and by 
Sasman and Cresci's method for turbulent flow. 
The nozzle is designed to produce uniform parallel 
flow at the nozzle exit in the smallest possible distance. 
Boundary-layer parameters are calculated for the ideal 
nozzle, and the final nozzle geometry is obtained by 
adding the displacement thickness to the ideal nozzle 
coordinates. The boundary-layer parameters are also 
used to calculate the after-mixing conditions down-
stream of the nozzle, assuming the flow mixes to a 
uniform state.
The computer program input consists essentially of 
the nozzle-exit Mach number, specific-heat ratio, nozzle 
angle, throat half-height, nozzle subsonic section co-
ordinates and corresponding pressure ratios, total temper-
ature and pressure, gas constant, and initial momentum 
or displacement thickness. The program gas properties 
are set for air; for other gases, changes are required to 
the program. The computer program output consists 
of the corrected nozzle coordinates, the principal bound-
ary-layer parameters, and the after-mixing conditions. 
Notes: 
1. This program is written in FORTRAN IV for use on 
the IBM-7094/7044 Direct Couple System. 
2. Inquiries concerning this program should be directed 
to:
COSMIC 
112 Barrow Hall 
University of Georgia 
Athens, Georgia 30601 
Reference: LEW-1 1636 
Source: Louis J. Goldman and

Michael R. Vanco
Lewis Research Center
(LEW-1 1636) 
Category 09, 06 
This document was prepared under the sponsorship of the National	 Government assumes any liability resulting from the use of the 
Aeronautics and Space Administration. Neither the United States 	 information contained in this document, or warrants that such use 
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Design of two-dimensional sharp-edged-throat supersonic nozzle with boundary-layer correction

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