A RELATION FOR SPECIFIC IMPULSE VERSUS BACK PRESSURE CHANGES AND OPTIMUM CONICAL NOZZLE EXPANSION RATIO ALGORITHM

Q: How can I download an article?

To download an article from SID, first log in to the site, search for the article title, and click on the 'Download Article' option.

Q: How can I download an ISI article?

To download an ISI article on SID, enter the keyword or article title in the search bar, view the relevant results, click on the desired article, and select the 'Download Article' option.

Q: How can I access the SID database?

To access the SID database, visit SID.ir, create an account, and log in to access scientific resources.

Q: Is downloading articles from SID free?

Some articles on SID are available for free, while others require payment. Details are specified on the article's page.

REZAEI VAHID; ABDOLLAHPOUR MOHAMMAD SALEH; MARDANI AMIR

مرکز اطلاعات علمی Scientific Information Database (SID) - Trusted Source for Research and Academic Resources

Journal Paper

Paper Information

Journal: Modares Mechanical Engineering Year:2016 | Volume:16 | Issue:9 Page(s): 307-317

Download Full-Text

Persian Verion

View:

1,085

Download:

Cites:

Information Journal Paper

Title

A RELATION FOR SPECIFIC IMPULSE VERSUS BACK PRESSURE CHANGES AND OPTIMUM CONICAL NOZZLE EXPANSION RATIO ALGORITHM

Author(s)

REZAEI VAHID | ABDOLLAHPOUR MOHAMMAD SALEH | MARDANI AMIR | Issue Writer Certificate

Keywords

SPECIFIC IMPULSEQ1

OPTIMUM EXPANSION RATIOQ1

BACK PRESSUREQ3

Abstract

The main objective of utilizing nozzles is to convert the chemical energy to kinetic energy producing thrust. A wide variety of parameters makes a significant impact on nozzle performance; one parameter that produces dramatic effect is BACK PRESSURE or ambient pressure. Basically, a nozzle designed for a specific BACK PRESSURE does not work properly when the engine is ascending. Consequently, designing of nozzles requires knowledge of full effect of BACK PRESSURE on engine performance. In this study, numerical simulation of three solid propellant nozzles has been conducted in several flight conditions.In other words, simulation have been done in some ambient pressures which represent specific flight altitudes. Numerical modeling has been conducted aiding commercial code FLUENT. k-e RNG turbulence model has been used for calculating turbulence interactions with the flow. Mass flow rate, chemical species, and chamber temperature have been used as the inlet boundary conditions based on engine specifications. Numerical results show a reasonable accuracy in comparison with experimental measurements. Estimating nozzle thrust level as a function of altitude increment is the primary goal of this study. Furthermore, with the aid of this relation and a MATLAB code for computing average SPECIFIC IMPULSE, OPTIMUM EXPANSION RATIO can be achieved based on a specified mission.

Cites

No record.

References

No record.

Cite

APA: Copy

REZAEI, VAHID, ABDOLLAHPOUR, MOHAMMAD SALEH, & MARDANI, AMIR. (2016). A RELATION FOR SPECIFIC IMPULSE VERSUS BACK PRESSURE CHANGES AND OPTIMUM CONICAL NOZZLE EXPANSION RATIO ALGORITHM. MODARES MECHANICAL ENGINEERING, 16(9), 307-317. SID. https://sid.ir/paper/179787/en

Vancouver: Copy

REZAEI VAHID, ABDOLLAHPOUR MOHAMMAD SALEH, MARDANI AMIR. A RELATION FOR SPECIFIC IMPULSE VERSUS BACK PRESSURE CHANGES AND OPTIMUM CONICAL NOZZLE EXPANSION RATIO ALGORITHM. MODARES MECHANICAL ENGINEERING[Internet]. 2016;16(9):307-317. Available from: https://sid.ir/paper/179787/en

IEEE: Copy

VAHID REZAEI, MOHAMMAD SALEH ABDOLLAHPOUR, and AMIR MARDANI, “A RELATION FOR SPECIFIC IMPULSE VERSUS BACK PRESSURE CHANGES AND OPTIMUM CONICAL NOZZLE EXPANSION RATIO ALGORITHM,” MODARES MECHANICAL ENGINEERING, vol. 16, no. 9, pp. 307–317, 2016, [Online]. Available: https://sid.ir/paper/179787/en

Related Journal Papers