Experimental Study of Axisymmetric Confined Jet Thrust Vector Control Nozzle Performance and Behavior PDF Download

Author: Peter G. Lambert (CAPT, USAF.)
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: Jerold H. Friddell (CAPT, USAF.)
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Category :
Languages : en
Pages :

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Author: Timothy M. Hawkes
Publisher:
ISBN:
Category :
Languages : en
Pages : 101

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An experimental study of the axial and vectoring performance of two - dimensional (2-D) confined jet thrust vector control (CJTVC) nozzles was performed. The effects of adding secondary injection ports and changing exit height and secondary injection port location were studied on several 2-D CJTVC nozzles. The axial and vectoring performance results for these nozzles were measured over a range of pressure ratios. An analytical method for predicting flow separation was found to be applicable to these nozzles. Guidelines for designing 2-D CJTVC nozzles, that can be vectored using secondary injection, were established.

Author: Jeffrey L. Caton
Publisher:
ISBN:
Category :
Languages : en
Pages : 168

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An experimental investigation of two-dimensional confined jet thrust vector control nozzles was performed. Thrust vector control was accomplished by using secondary flow injection in the diverging section of the nozzle. Schlieren photographs and video tapes were used to study flow separation and internal shock structures. Nozzle performance parameters were determined for nozzle flow with and without secondary flows. These parameters included nozzles forces, vector angles, thrust efficiencies, and flow switching response times. Vector angles as great as 18 degrees with thrust efficiencies of 0.79 were measured. Several confined jet nozzles with variations in secondary flow port design were tested and results were compared to each other. Converging-diverging nozzles of similar design to the confined jet nozzles were also tested and results were compared to the confined jet nozzle results. Existing prediction models for nozzle side to axial force ratio were evaluated. A model for nozzle total forces based on shock losses that predicted values very close to actual results was developed. Keywords: Two dimensional flow; Flow visualization; Control jets; Rocket nozzles; Nozzle gas flow; Reconvergent nozzles. Theses.

Author: Robert W. Ryan (MAJ, USAF.)
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: Timothy A. Talda (2LT, USAF.)
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Category : Rocket engines
Languages : en
Pages :

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Author: James W. Cates
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ISBN:
Category :
Languages : en
Pages : 68

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In this experimental investigation, the performance parameters considered were axial force, side force, and vector angle. Variables included primary pressure, exit-to-throat area ratio, and exit-to-throat axial length. With each test configuration, it was possible to define specific operating modes where the flow was oscillatory, vectored/switchable, and vectored/unswitchable. Only one test configuration yielded a stable axial flow on which secondary injection could be used to study vectoring. Switchable flows existed only at low pressure below the range of test pressures making it impossible to study switching characteristics. Because the flows were attached over the entire range of test pressures, geometric effects were based on the study of these attached flows. Results indicate that the theoretical equations for predicting wall separation points in unconfined nozzles do not accurately predict the separation points in confined jet nozzles. Small variations in axial length, as examined in this study, had a minimal impact on nozzle performance. Primary pressure and exit-to-throat area ratio have the most significant impact on two-dimensional nozzle performance. Keywords: Two dimensional flow; Flow visualization; Axial thrust. (Theses).

Author: R. E. Fitzgerald
Publisher:
ISBN:
Category :
Languages : en
Pages : 73

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This report describes the experimental development effort on a confined jet thrust vector control (CJTVC) nozzle. This effort consisted of cold flow testing with gaseous nitrogen to determine the influence of geometric variables on nozzle performance, and hot gas testing and analysis of nozzle materials. The cold gas testing was done with nozzles so configured that every geometric parameter influencing performance could be readily varied. The primary approach used throughout cold flow testing was to vary geometry and determine the influences on measured axial and side force generated by the CJTVC nozzle. The results of the cold flow testing, the design data generated, and the materials experience gained are presented in this report. (Author).

Author: J. H. Friddell
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: Eugene P. Symons
Publisher:
ISBN:
Category : Laminar flow
Languages : en
Pages : 28

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An experimental investigation was conducted to determine dynamic characteristics of a circular, fully developed, laminar free jet. Complete velocity profiles are presented at Reynolds numbers of 437 and 1839 at 0, 3, 6, 10, 15, and 25 diameters from the nozzle exit. Centerline velocity decay was obtained over a range of Reynolds numbers from 255 to 1839. Also presented are the angles of spread associated with the diffusion of the jet downstream of the nozzle. Where possible, results are compared with those obtained for laminar jets having an initially flat or uniform velocity profile at the nozzle exit.