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Suppression of the ignition overpres...

Canabal, Francisco, III.

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Suppression of the ignition overpressure generated by launch vehicles.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Suppression of the ignition overpressure generated by launch vehicles./
Author:	Canabal, Francisco, III.
Description:	102 p.
Notes:	Source: Dissertation Abstracts International, Volume: 65-02, Section: B, page: 0858.
Contained By:	Dissertation Abstracts International65-02B.
Subject:	Engineering, Aerospace. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3122315

Suppression of the ignition overpressure generated by launch vehicles.
Canabal, Francisco, III.

Suppression of the ignition overpressure generated by launch vehicles. - 102 p.

Source: Dissertation Abstracts International, Volume: 65-02, Section: B, page: 0858.

Thesis (Ph.D.)--The University of Alabama in Huntsville, 2004.

The main objective of this study is to gain an understanding of the mechanisms responsible for the suppression of the ignition overpressure observed when water is added to a rocket engine exhaust. A simplified launch-vehicle/launch-pad configuration of relevant importance is selected for this study. This configuration is then numerically simulated with a representative engine start-up sequence and a series of water addition configurations. A total of eleven water addition configurations was studied. The study demonstrated that ignition overpressure is strongly affected by the cooling of the plume and the amount of obstruction restricting the expansion of the plume. Also, the study suggests the existence of an optimal water addition rate with a weak dependence on the water nozzle pressure drop.Subjects--Topical Terms:

1018395
Engineering, Aerospace.

Suppression of the ignition overpressure generated by launch vehicles.
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005 20041216102949.5
008 130614s2004 eng d
035 $a (UnM)AAI3122315
035 $a AAI3122315
040 $a UnM $c UnM
100 1 $a Canabal, Francisco, III. $3 1900524
245 1 0 $a Suppression of the ignition overpressure generated by launch vehicles.
300 $a 102 p.
500 $a Source: Dissertation Abstracts International, Volume: 65-02, Section: B, page: 0858.
500 $a Adviser: Kader Frendi.
502 $a Thesis (Ph.D.)--The University of Alabama in Huntsville, 2004.
520 $a The main objective of this study is to gain an understanding of the mechanisms responsible for the suppression of the ignition overpressure observed when water is added to a rocket engine exhaust. A simplified launch-vehicle/launch-pad configuration of relevant importance is selected for this study. This configuration is then numerically simulated with a representative engine start-up sequence and a series of water addition configurations. A total of eleven water addition configurations was studied. The study demonstrated that ignition overpressure is strongly affected by the cooling of the plume and the amount of obstruction restricting the expansion of the plume. Also, the study suggests the existence of an optimal water addition rate with a weak dependence on the water nozzle pressure drop.
590 $a School code: 0278.
650 4 $a Engineering, Aerospace. $3 1018395
650 4 $a Physics, Fluid and Plasma. $3 1018402
650 4 $a Physics, Acoustics. $3 1019086
690 $a 0538
690 $a 0759
690 $a 0986
710 2 0 $a The University of Alabama in Huntsville. $3 1017884
773 0 $t Dissertation Abstracts International $g 65-02B.
790 1 0 $a Frendi, Kader, $e advisor
790 $a 0278
791 $a Ph.D.
792 $a 2004
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3122315