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Performance Of Several Conical Convergent Divergent Rocket Type Exhaust Nozzles

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Performance of Several Conical Convergent Divergent Rocket Type Exhaust Nozzles

Performance of Several Conical Convergent Divergent Rocket Type Exhaust Nozzles Book
Author : C. E. Campbell
Publisher : Unknown
Release : 1960
ISBN : 0987650XXX
File Size : 37,5 Mb
Language : En, Es, Fr and De

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Book Summary :

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.

Performance of Several Conical Convergent divergent Rocket type Exhaust Nozzles

Performance of Several Conical Convergent divergent Rocket type Exhaust Nozzles Book
Author : C. E. Campbell,J. M. Farley
Publisher : Unknown
Release : 1960
ISBN : 0987650XXX
File Size : 50,8 Mb
Language : En, Es, Fr and De

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Book Summary :

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.

NASA Technical Note

NASA Technical Note Book
Author : Anonim
Publisher : Unknown
Release : 1962
ISBN : 0987650XXX
File Size : 34,6 Mb
Language : En, Es, Fr and De

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Book Summary :

Download NASA Technical Note book written by and published by with total hardcover pages 816 . Available in PDF, EPUB, and Kindle, read book directly with any devices anywhere and anytime.

Experimental Study of Effects of Geometric Variables on Performance of Conical Rocket Engine Exhaust Nozzles

Experimental Study of Effects of Geometric Variables on Performance of Conical Rocket   Engine Exhaust Nozzles Book
Author : Harry E. Bloomer,Robert J. Antl,Pqul E. Renas
Publisher : Unknown
Release : 1961
ISBN : 0987650XXX
File Size : 42,9 Mb
Language : En, Es, Fr and De

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Book Summary :

Download Experimental Study of Effects of Geometric Variables on Performance of Conical Rocket Engine Exhaust Nozzles book written by Harry E. Bloomer,Robert J. Antl,Pqul E. Renas and published by with total hardcover pages 61 . Available in PDF, EPUB, and Kindle, read book directly with any devices anywhere and anytime.

Performance of Several Method of Characteristics Exhaust Nozzles

Performance of Several Method of Characteristics Exhaust Nozzles Book
Author : John M. Farley
Publisher : Unknown
Release : 1960
ISBN : 0987650XXX
File Size : 30,7 Mb
Language : En, Es, Fr and De

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Book Summary :

Download Performance of Several Method of Characteristics Exhaust Nozzles book written by John M. Farley and published by with total hardcover pages 40 . Available in PDF, EPUB, and Kindle, read book directly with any devices anywhere and anytime.

NASA Technical Paper

NASA Technical Paper Book
Author : Anonim
Publisher : Unknown
Release : 1978
ISBN : 0987650XXX
File Size : 47,7 Mb
Language : En, Es, Fr and De

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Book Summary :

Download NASA Technical Paper book written by and published by with total hardcover pages . Available in PDF, EPUB, and Kindle, read book directly with any devices anywhere and anytime.

Experimental Study of Effects of Geometric Variables on Performance of Contoured Rocket Engine Exhaust Nozzles

Experimental Study of Effects of Geometric Variables on Performance of Contoured Rocket Engine Exhaust Nozzles Book
Author : Harry E. Bloomer,Robert J. Antl,Paul E. Renas
Publisher : Unknown
Release : 1962
ISBN : 0987650XXX
File Size : 47,9 Mb
Language : En, Es, Fr and De

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Book Summary :

Download Experimental Study of Effects of Geometric Variables on Performance of Contoured Rocket Engine Exhaust Nozzles book written by Harry E. Bloomer,Robert J. Antl,Paul E. Renas and published by with total hardcover pages 27 . Available in PDF, EPUB, and Kindle, read book directly with any devices anywhere and anytime.

Theoretical Performance of Hydrogen oxygen Rocket Thrust Chambers

Theoretical Performance of Hydrogen oxygen Rocket Thrust Chambers Book
Author : Gilbert K. Sievers,William A. Tomazic,George R. Kinney
Publisher : Unknown
Release : 1961
ISBN : 0987650XXX
File Size : 31,6 Mb
Language : En, Es, Fr and De

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Book Summary :

Theoretical rocket performance data for the propellant combination of liquid hydrogen and liquid oxygen are presented in convenient graphical forms to permit rapid determination of specific impulse, vacuum specific impulse, and characteristic velocity. Data are presented for both frozen and equilibrium composition during expansion for chamber pressures of 15, 30, 60, 150, 300, 600, 900 and 1200 pounds per square inch absolute over a wide range of percent fuel from approximately 8 to 34 and area ratios to approximately 300. For rapid calculation of the theoretical nozzle performance with over- or under- expansion, separated flow, and introduction of propellants at different initial conditions or heat loss from the combustion chamber, the following theoretical data are also presented: combustion-chamber temperature, nozzle-exit temperature, and the ratio of chamber-pressure to nozzle-exit pressure. An easy method is given for estimating theoretical specific impulse at chamber pressures other than those presented.