Analytical and Experimental Investigation of Performance of Supersonic Ejector Nozzles PDF Download
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Author: Shen Huili
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
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Author: Shen Huili
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
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Author: Alfred C. Pinchak
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 0
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A series of experimental tests were performed with air:air constant area supersonic injectors, and typical results are presented here. Data were taken with secondary mass flows, both larger and smaller in magnitude than the primary mass flow. One of the constant area injectors produced a remarkable pumping efficiency of 30% with equal mass flows in the primary and secondary. A special constant area mixing tube was constructed and tested. This test indicated a ratio 5
Author: Roy Nathan Guile
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 338
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 376
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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Donald L. Weiss
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Author: Sheridan D. Johnston
Publisher:
ISBN:
Category : Supersonic diffusers
Languages : en
Pages : 52
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 216
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 109
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This dissertation presents the results of an experimental investigation and analysis of the supersonic rectangular over-expanded flow of single and two-phase flows. Recent interest in rectangular supersonic jets is motivated by the need to reduce plume length and acoustically excited structural loads in the exhaust system of high performance aircrafts. Semi-periodic shock structures form in the jet plumes of these vehicles during low speed flight at off design conditions. These shock cells affect the jet velocity and temperature decay as well as the jet spread rate and its acoustic field. The flow regimes and shock structure in the plume was characterized for jets in quiescent atmosphere at over-expanded conditions. Instantaneous and phase average schlieren/shadowgraph images of the internal flow and the jets are presented to show the over-expanded shock structure and jet spread rate at different nozzle pressure ratios ranged from 1.6 to 9.5. A high-pressure particle feeders have been constructed to steady feed the dispersed large particles and the seeding particle for LDA measurements at different particle loading rates. Schlieren pictures of the jets are presented to show the shock structure and jet spread rate. LDV measurements are presented for the jet flow field and the centerline velocity decay. The results indicate that the rectangular supersonic jet spread rate is greater along the minor axis and increases with the nozzle pressure ratio. The individual shock cell length, as well as, the total number of shock cells within the jet plume were found to increase with nozzle pressure ratio. In two-phase rectangular jets of gas and dispersed solid particles the shock strength was found to attenuate with increased particle loading. The design, construction and initial shakedown of the facility has been accomplished. The effort required to reach this stage has been greater than initially expected. Further more detailed data acquisitions and measurements will be accomplished in future studies.
Author: Edsel R. Glasgow
Publisher:
ISBN:
Category : Airframes
Languages : en
Pages : 714
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An experimental and analytical investigation of the installed thrust and drag of various isolated nozzle and twin-nozzle/aftbody configurations indicated that empirical correlations provide the best means of predicting aft- end performance, especially for the early stages of the aircraft design. Both subsonic and transonic isolated nozzle drag data were correlated using IMS (integral mean slope) as the geometric parameter. A correlation of twin-nozzle/aftbody drag data at subsonic and transonic speeds was developed by combining Spreiter's transonic similarity parameters with the IMS of the equivalent body of revolution. A correlation of inviscid MOC pressure drag, achieved through use of IMS combined with similarity parameters obtained from linearized supersonic flow theory, provided an accurate and rapid means of estimating drag for arbitrary axisymmetric boattail contours at supersonic speeds. Twin-nozzle/aftbody drag data at supersonic speeds was correlated with the equivalent body drag obtained from the axisymmetric MOC correlation. Improved thrust and drag performance was obtained by modifying the aft-end design of five selected aircraft configurations. The rationale for these modifications was derived from design guidelines and criteria developed during the program. Improvements in mission radius for a fixed takeoff gross weight aircraft were obtained, in general, by utilizing convergent-divergent nozzles, a horizontal wedge interfairing with the trailing edge terminating at the exit plane of the nozzles, a single vertical stabilizer, and a narrow lateral nozzle spacing.
Author: Bernhard H. Anderson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 54
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