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Effect of inlet boundary-layer thickness and structure on heat transfer in a supersonic nozzle.
Inlet boundary layer thickness and structure effects on heat transfer in supersonic nozzle
Turbulent-flow separation criteria for overexpanded supersonic nozzles
A comprehensive compilation of available turbulent flow separation data for overexpanded supersonic nozzles is presented with a discussion of correlation techniques, and prediction methods. Data are grouped by nozzle types: conical, contoured, and two dimensional wedge. Correlation of conical nozzle separation is found to be independent of nozzle divergence half-angle above the 9 deg, whereas the contoured nozzle data follow a different correlation curve. Zero pressure gradient prediction techniques are shown to predict adequately the higher divergence angle conical separation data, and an empirical equation is given for the contoured nozzle data correlation. Flow conditions for which the correlations are invalid are discussed and bounded. A nozzle boundary layer transition criterion is presented which can be used to show that much of the noncorrelating data in the literature are concerned with nonturbulent separation and which explains the previously reported external flow effects on nozzle separation.
Flow coefficients for supersonic nozzles with comparatively small radius of curvature throats
Small curvature radius/throat radius ratio supersonic nozzles mass flow rate coefficients at high Reynolds numbers, appraising isentropic flow prediction methods
Equations for the design of two-dimensional supersonic nozzles
Equations are presented for obtaining the wall coordinates of two-dimensional supersonic nozzles. The equations are based on the application of the method of characteristics to irrotational flow of perfect gases in channels. Curves and tables are included for obtaining the parameters required by the equations for the wall coordinates. A brief discussion of characteristics as applied to nozzle design is given to assist in understanding and using the nozzle-design method of this report. A sample design is shown.
Computer program for design of two dimensional supersonic nozzle with sharp edged throat
FORTRAN 4 program for computerized design of two dimensional supersonic nozzles with sharp edged throats
Transonic flowfield in a supersonic nozzle with small throat radius of curvature.
Internal flow measurements in transonic region of supersonic nozzle with small throat radius of curvature compared with prediction data
Heat-transfer measurements in the shock-induced flow separation region in a supersonic nozzle.
Pressure and semilocal wall heat flux measurements in shock induced flow separation region in supersonic nozzle, noting shock waves-flow interaction
Influence of contraction section shape and inlet flow direction on supersonic nozzle flow and performance.
Wall static pressure measurements and performance parameters are presented for axisymmetric supersonic nozzles with relatively steep convergent sections and comparatively small radius-of-curvature throats. The nozzle walls were essentially adiabatic. These results are compared with those obtained in other nozzles tested previously to appraise the influence of contraction shape on performance. Both the flow coefficient and the thrust were less than the corresponding values for one-dimensional, isentropic, plane flow for both the axial and radial inflow nozzles considered, but the specific impulse, the most important performance parameter, was found to be relatively unchanged. The thrust decrement for the axial inflow nozzles was established primarily by the shape of the contraction section, and could be estimated reasonably well from a conical sink flow consideration. The radial inflow nozzle has a potential advantage from a cooling point of view if used in a rocket engine.
Experimental evaluation of expendable supersonic nozzle concepts
Exhaust nozzles for expendable supersonic turbojet engine missile propulsion systems are required to be simple, short and compact, in addition to having good broad-range thrust-minus-drag performance. A series of convergent-divergent nozzle scale model configurations were designed and wind tunnel tested for a wide range of free stream Mach numbers and nozzle pressure ratios. The models included fixed geometry and simple variable exit area concepts. The experimental and analytical results show that the fixed geometry configurations tested have inferior off-design thrust-minus-drag performance in the transonic Mach range. A simple variable exit area configuration called the Axi-Quad nozzle, combining features of both axisymmetric and two-dimensional convergent-divergent nozzles, performed well over a broad range of operating conditions. Analytical predictions of the flow pattern as well as overall performance of the nozzles, using a fully viscous, compressible CFD code, compared very well with the test data.
An experimental investigation of the escape of dissociated gases through supersonic nozzles
Shock tube studies of flow of thermally dissociated oxygen, nitrogen, and carbon dioxide gases through supersonic nozzles
Calculation of the recombination rate constants of diatomic gases according to the Mach number of the flow at the exit of a supersonic nozzle
Calculation of recombination rate constants of diatomic molecules according to Mach number of flow at supersonic nozzle exit
Computer program for design of two-dimensional sharp-edged-throat supersonic nozzle with boundary layer correction
FORTRAN 4 computer program for design of sharp-edged-throat supersonic nozzles with boundary layer correction
Modification of a three-dimensional supersonic nozzle analysis and comparison with experimental data
A computer program previously developed to analyze three-dimensional supersonic nozzles by the method of characteristics has been modified to study less restrictive nozzle geometries and nonuniform inlet conditions. An example indicates that a one-dimensional calculation that uses an averaged initial profile may be significantly in error. A comparison between the analysis and the data from a three-dimensional experiment shows generally good agreement between the two.
Design Data for Graphical Construction of Two-Dimensional Sharp-Edge-Throat Supersonic Nozzles
Design data are presented for the graphical construction of two-dimensional sharp-edge-throat supersonic nozzles of minimum length for test-section Mach numbers from 1.20 to 10.00. The method of characteristics used in the design is briefly reviewed.
Flow field for an underexpanded, supersonic nozzle exhausting into an expansive launch tube
Static pressure distributions along the launcher wall and pitot pressure measurements from the annular region between the rocket and the launcher were made as an underexpanded supersonic nozzle exhausted into an expansive launch tube. The flow remained supersonic along the entire length of the launcher for all nozzle locations studied.
Performance of a constricted-arc discharge in a supersonic nozzle.
Plasma generator is described which produces supersonic gas flow at high enthalpies by passage of constricted-arc discharge through nozzle
Investigation of Net-Thrust and Base-Pressure Characteristics of Cylindrical Afterbodies with Clustered Supersonic Nozzles at Transonic Mach Numbers
A wind-tunnel investigation has been conducted at Mach numbers from 0.9 to 1.4 to determine the net-thrust and base-pressure characteristics of cylindrical afterbodies having clustered supersonic nozzles. The design Mach numbers of the nozzles were 2.0 and 2.5 and the number of clustered nozzles ranged from two to six. The nozzles had throat-to- base diameter ratios of 0.155, 0.225, 0.278, and 0.320. Some models were tested with various configurations of extended, shrouded, flush, and canted nozzles. The nozzles discharged unheated air from the base at ratios of jet total pressure to free-stream static pressure ranging from 1 to approximately 20. The results of this investigation showed that both the ratio of total exit area to base area and the number of jets affect the net-thrust factor to a significant degree for the extended-nozzle configurations. Good net-thrust factors were obtained with all the model configurations near the design jet total-pressure ratio; however, the extended-nozzle configuration had the highest net-thrust factor over the test jet total- pressure-ratio range. Canting the twin nozzles outward resulted in a favorable thrust factor over a limited jet total-pressure-ratio range, and surrounding the nozzles with a single shroud reduced thrust factors for the range of jet total-pressure ratio of this investigation.