Comparison of Performance of a Double-Cornered Plug Nozzle with a Conventional Convergent-Divergent Rocket Nozzle PDF Download
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Author: Arnold T. Stokes
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
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Book Description
The report presents performance data for double-cornered plug nozzles for comparison with convergent-divergent nozzles. A conventional convergent- divergent (C-D) nozzle was used to develop the propellant charge, ignition and ballistics, and as a baseline for plug nozzle performance evaluation. (Author).
Author: Arnold T. Stokes
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
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Book Description
The report presents performance data for double-cornered plug nozzles for comparison with convergent-divergent nozzles. A conventional convergent- divergent (C-D) nozzle was used to develop the propellant charge, ignition and ballistics, and as a baseline for plug nozzle performance evaluation. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
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Book Description
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: C. E. Campbell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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Book Description
An investigation was conducted to obtain nozzle performance data with relatively large-scale models at pressure ratios as high as 120. Conical convergent-divergent nozzles with divergence angles alpha of 15, 25, and 29 deg. were each tested at area ratios of approximately 10, 25, and 40. Heated air (1200 F) was supplied at the nozzle inlet at pressures up to 145 pounds per square inch absolute and was exhausted into quiescent air at pressures as low as 1.2 pounds per square inch absolute. Thrust ratios for all nozzle configurations are presented over the range of pressure ratios attainable and were extrapolated when possible to design pressure ratio and beyond. Design thrust ratios decreased with increasing nozzle divergence angle according to the trend predicted by the (1 + cos alpha)/2 parameter. Decreasing the nozzle divergence angle resulted in sizable increases in thrust ratio for a given surface-area ratio (nozzle weight), particularly at low nozzle pressure ratios. Correlations of the nozzle static pressure at separation and of the average static pressure downstream of separation with various nozzle parameters permitted the calculation of thrust in the separated-flow region from unseparated static-pressure distributions. Thrust ratios calculated by this method agreed with measured values within about 1 percent.
Author: Albert J. Pavli
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
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Book Description
Author: H. George Krull
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 20
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Book Description
An investigation was conducted to determine the effect on performance of two methods (iris outer shell and translatable outer shell or translatable plug) of throat-area modulation of two convergent plug nozzles. These nozzles included a 30 degree conical plug nozzles and an isentropic plug nozzle. Data were obtained over a range of pressure ratios from about 1.5 to 30.
Author:
Publisher:
ISBN:
Category : Technology
Languages : en
Pages : 1352
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Book Description
Author: Laurence W. Gertsma
Publisher:
ISBN:
Category : Ejector pumps
Languages : en
Pages : 48
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Book Description
Author: Donald F. Schultz
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
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Book Description
A full-scale annular combustor was operated with simplex fuel nozzles of three flow ranges and with dual-orifice fuel nozzles. The dual-orifice nozzles provided combustion efficiencies within 2 to 3 percent of the peak values obtained with any of the simplex atomizers. A wide range of operating conditions including altitude relight, simulated takeoff, Mach 2.7 cruise, and Mach 3.0 cruise were studied. Measurements were made of combustion efficiency, pattern factor , flame radiation, smoke emission, and response to rapid increase in fuel flow. Fuel heated to 300 [degree] F (423 K) was used in many of the tests; heated fuel usually increased combustion efficiency.
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 240
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Book Description
Author: H. George Krull
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 24
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Book Description
An evaluation of the internal performance characteristics of short nozzles designed by the method of characteristics was obtained over a range of nozzle pressure ratios from 1.5 to 22.
