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Three-dimensional supersonic nozzles and inlets of arbitrary exit cross section

Description: From Summary: "A method is presented for obtaining three-dimensional unsymmetric supersonic nozzles and inlets from known axisymmetric flows. Stream-lines bounding the desired exit shape are traced through the known basic flow solution to give the required unsymmetric wall contours. Several examples are given."
Date: April 1952
Creator: Evvard, John C. & Maslen, Stephen H.
Partner: UNT Libraries Government Documents Department

Investigation at Mach number 1.91 of spreading characteristics of jet expanding from choked nozzles

Description: Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date: February 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

Annular-jet ejectors

Description: From Summary: "Included in the report are the results of total-pressure surveys made at downstream ends of the mixing tubes."
Date: November 1949
Creator: Reid, Elliott G
Partner: UNT Libraries Government Documents Department

Analysis of heat addition in a convergent-divergent nozzle

Description: From Introduction: "The purpose of this report is to treat analytically heat addition heat addition to a divergent stream with initially sonic flow and to employ the results thus obtained in evaluating the effect of delayed combustion on convergent-divergent nozzle performance."
Date: April 1953
Creator: Hearth, Donald P. & Perchonok, Eugene
Partner: UNT Libraries Government Documents Department

An accurate and rapid method for the design of supersonic nozzles

Description: From Introduction: "This report presents a computational procedure which provides for the rapid and accurate calculation of any streamline in a series of special flows. Detailed information is given on the boundary conditions and equations used for computing the characteristic nets and stream function."
Date: February 1955
Creator: Beckwith, Ivan E. & Moore, John A.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of performance of variable-throat extended-plug-type nozzles over wide range of nozzle pressure ratios

Description: From Summary: "As part of an overall program for the experimental investigation of large-scale jet nozzles, a preliminary evaluation of the internal performance characteristics of several variable-throat extended-plug-type nozzles was obtained over a range of nozzle pressure rations from 2 to 15 with nozzle throat variations as great as 2:1. The extended-plug nozzle attained peak thrust coefficients as high as those which have been attained with fixed-geometry convergent-divergent nozzles. The thrust coefficients of the extended-plug nozzles were relatively insensitive to both nozzle pressure ratio and throat area over the range investigated."
Date: February 5, 1954
Creator: Ciepluch, Carl C.; Krull, H. George & Steffen, Fred W.
Partner: UNT Libraries Government Documents Department

Internal performance characteristics of variable-throat plug- and vaned-type convergent-divergent nozzles

Description: Investigation of the internal performance characteristics of three types of variable-throat convergent-divergent nozzles over a wide range of pressure ratios. Only small differences in peak thrust coefficient between the three types of variable-throat convergent-divergent nozzles were obtained.
Date: June 23, 1953
Creator: Krull, H. George; Steffen, Fred W. & Ciepluch, Carl C.
Partner: UNT Libraries Government Documents Department

Effects of several geometric variables on internal performance of short convergent-divergent exhaust nozzles

Description: Report presenting an investigation to determine the effects on internal performance of several geometric variables intended to produce a short, high-performance convergent-divergent nozzle. Some of the characteristics investigated included variations in the throat-contour radius, combinations of the shape of the convergent section and throat-contour radius, divergence angle, and shape of the divergent section.
Date: February 18, 1955
Creator: Steffen, Fred W.; Krull, H. George & Schmiedlin, Ralph F.
Partner: UNT Libraries Government Documents Department

Comparison of two methods of modulating the throat area of convergent plug nozzles

Description: Report presenting an investigation to determine the effect on performance of two methods of throat-area modulation of two convergent plug nozzles. Data were obtained over a range of pressure ratios. Results regarding the performance of the translatable outer-shell-type plug nozzle, performance of the iris-outer-shell-type plug nozzles, sensitivity to throat-area variation, and air-flow parameter are provided.
Date: May 11, 1955
Creator: Krull, H. George & Beale, William T.
Partner: UNT Libraries Government Documents Department

Performance characteristics of one convergent and three convergent-divergent nozzles

Description: Report presenting the performance characteristics of one convergent and three convergent-divergent nozzles obtained over a range of nozzle pressure ratios. Results regarding one-dimensional flow theory and the performance characteristics themselves are provided.
Date: September 29, 1952
Creator: Krull, H. George & Steffen, Fred W.
Partner: UNT Libraries Government Documents Department

Effect of ejector performance of varying diameter ratio by simulated iris flaps

Description: Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel at several free-stream Mach numbers for a range of primary-nozzle pressure ratios and secondary weight-flow ratios to determine the effects on performance of varying the ejector diameter ratio by simulated iris flaps. Results indicated that increases in ejector gross force and secondary-to-primary total-pressure ratio were obtained subsonically when diameter ratio was reduced, thus reducing overexpansion losses.
Date: April 21, 1955
Creator: Valerino, Alfred S. & Stitt, Leonard E.
Partner: UNT Libraries Government Documents Department

Effect of several design variables on internal performance of convergent-plug exhaust nozzles

Description: Numerous experiments were conducted to determine factors which affect the internal performance of convergent-plug exhaust nozzles. The results of these experiments, which include effects of such things as plug shape, nozzle inlet Mach number, and outer-shell characteristics, provide a basis for optimum desifn from the standpoint of weight and size. The results also show performance penalties which can result when the nozzle is too small.
Date: October 29, 1956
Creator: Krull, H. George; Beale, William T. & Schmiedlin, Ralph F.
Partner: UNT Libraries Government Documents Department

Effect of plug design on performance characteristics of convergent-plug exhaust nozzles

Description: Report presenting an evaluation of the internal performance characteristics of several plug-type nozzles over a range of pressure ratios from 1.5 to 30. Results regarding isentropic plug nozzles, conical plug nozzles, the effect of throat and throat-approach section on performance, and air-flow parameter are provided.
Date: October 25, 1954
Creator: Krull, H. George & Beale, William T.
Partner: UNT Libraries Government Documents Department

Matching of auxiliary inlets to secondary-air requirements of aircraft ejector exhaust nozzles

Description: Report presenting an analysis of the problems associated with matching secondary-air requirements of ejector exhaust nozzles and auxiliary inlets has been made for free-stream Mach numbers up to 2.0. The analysis indicated that inlets located in the free stream supply higher pressure recovery than ejectors generally require for optimum net internal thrust at Mach numbers above about 1.4. Net-thrust gains can be achieved by immersing the auxiliary inlet in a boundary layer where the inlet-momentum penalty is less.
Date: August 16, 1955
Creator: Hearth, Donald P.; Englert, Gerald W. & Kowalski, Kenneth L.
Partner: UNT Libraries Government Documents Department

Investigation of thrust and drag characteristics of a plug-type exhaust nozzle

Description: From Summary: "An investigation was conducted in the 8- by 6-foot supersonic wind tunnel on the external and internal characteristics of a plug-type exhaust nozzle. Two positions of the center plug, one simulating a convergent nozzle and the other a convergent-divergent nozzle, were investigated. Data were obtained at free-stream Mach numbers of 0.1, 0.6, 1.6, and 2.0 over a pressure-ratio range of 1 to 20 and angles of attack of zero and 8 degrees. Results of this investigation indicated that the plug nozzle had thrust-minus-drag performance over the entire pressure-ratio range comparable with equivalent conventional nozzles."
Date: February 19, 1954
Creator: Hearth, Donald P. & Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department

Investigation of a two-step nozzle in an 11-inch hypersonic tunnel

Description: Report discussing flow surveys made of several nozzles using two 2-dimensional steps at Mach number 6.98. Results regarding wall-pressure surveys, disturbance patterns in expansion, total-pressure survey, temperature recovery, and general nozzle characteristics are provided.
Date: October 25, 1949
Creator: McLellan, Charles H.; Williams, Thomas W. & Bertram, Mitchel H.
Partner: UNT Libraries Government Documents Department

The design of variable Mach number asymmetric supersonic nozzles by two procedures employing inclined and curved sonic lines

Description: Report presenting two theoretical procedures for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One is for Mach numbers less than approximately 3 and one is for Mach numbers greater than 3.
Date: March 1953
Creator: Syvertson, Clarence A. & Savin, Raymond C.
Partner: UNT Libraries Government Documents Department

Analytical investigation of turbines with adjustable stator blades and effect of these turbines on jet-engine performance

Description: From Introduction: "A comparison is also made of the actual performance of two contemporary jet engines with estimated performance, assuming the engines were equipped with adjustable-angle stators and adjustable exhaust nozzles. Charts are presented that aid in estimating the performance of adjustable-stator turbines."
Date: July 17, 1950
Creator: Silvern, David H & Slivka, William R
Partner: UNT Libraries Government Documents Department

The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75

Description: From Introduction: "This paper presents the basic design method and experimental results of calibration of a nozzle which was constructed to conform to the analytically determined ordinates."
Date: April 1953
Creator: Burbank, Paige B. & Byrne, Robert W.
Partner: UNT Libraries Government Documents Department

The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section

Description: From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included."
Date: June 1952
Creator: Beckwith, Ivan E; Ridyard, Herbert W & Cromer, Nancy
Partner: UNT Libraries Government Documents Department

Experimental behavior of pentaborane-air combustion products during expansion in a convergent-divergent nozzle

Description: Report presenting an evaluation of the postcombustion behavior of boric oxide using pentaborane-air mixtures burned to completion at a combustor pressure of 3 atmospheres expanded through a convergent-divergent nozzle. Results regarding the symmetry of flow in nozzle, behavior of liquid boric oxide in nozzle, abrupt condensation phenomena, effect of abrupt condensation on performance, and effect of oxide films are provided.
Date: February 18, 1958
Creator: Branstetter, J. Robert & Setze, Paul C.
Partner: UNT Libraries Government Documents Department

Experimental investigation of flow in an annular cascade of turbine nozzle blades of constant discharge angle

Description: The experimental performance of turbine nozzle blades designed for a constant discharge angle was investigated at discharge hub Mach numbers of 1.18, 1.31, and 1.41. Flow characteristics are presented in terms of energy losses, angle gradients, and secondary flow effects. Blade efficiency decreased from 0.983 to 0.978 with increasing Mach number in the range investigated while angle variations in the loss regions became very large, indicating poorer blade performance than efficiency implies.
Date: March 3, 1952
Creator: Kofskey, Milton G.; Rohlik, Harold E. & Monroe, Daniel E.
Partner: UNT Libraries Government Documents Department