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The bell or contour shape is designed to impart a large angle expansion for the gases right after the throat. The nozzle is then curved back in to give a nearly straight flow of gas out the nozzle opening. The contour used is rather complex. The large expansion section near the throat causes
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An ideal nozzle would direct all of the gases generated in the combustion chamber straight out the nozzle. That would mean the momentum of the gases would be axial, imparting the maximum thrust to the rocket. In fact, there are some non-axial components to the momentum. In terms of a
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nozzle. It has a high angle expansion section (20 to 50 degrees) right behind the nozzle throat; this is followed by a gradual reversal of nozzle contour slope so that at the nozzle exit the divergence angle is small, usually less than a 10 degree half angle.
155:. A properly designed nozzle will have these two sets of shock waves coincide and cancel each other out. In this way, the bell is a compromise between the two extremes of the conical nozzle since it minimizes weight while maximizing performance.
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G.V.R. Rao, "Recent development in rocket nozzle configurations". Journal
American Rocket Society Vol. 31 Number 11 November 1961. Library of Congress call number TL 780.A613
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G.V.R. Rao, "Approximation of optimum thrust nozzle contours". Journal
American Rocket Society Vol. 30 Number 6 June 1960. Library of Congress call number TL 780.A613
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G.V.R. Rao
Contoured Rocket Nozzles. Ninth annual congress of the International Astronautical Federation 1958. Library of Congress call number TL 787.I44
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G.V.R. Rao, "Exhaust nozzle contour for optimum flight". Jet
Propulsion Vol. 28 number 6 1958. Library of Congress call number TL 780.A613
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The most important design issue is to contour the nozzle to avoid oblique shocks and maximize performance.
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expansion shock waves. The reversal of the slope to bring the exit to near zero degrees causes compression
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DEPARTMENT OF MECHANICAL AND AEROSPACE ENGINEERING NORTH CAROLINA STATE UNIVERSITY Raleigh, N.C.
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A STUDY OF NACA AND NASA PUBLISHED INFORMATION OF PERTINENCE IN THE DESIGN OF LIGHT AIRCRAFT
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Test firing of Space
Shuttle main engine (whose engine nozzle is very close in shape to optimal)
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with working out the mathematics of the optimal bell nozzle design in 1955, while working at
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Rocket
Propulsion Elements: An Introduction to the Engineering of Rockets
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216:(6th ed.). Wiley-Interscience. p. 636.
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134:is probably the most commonly used shaped
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189:Williams, James C. (1970).
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177:References
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270:See also
301:Nozzles
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