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Hypersonic Stagnation Point Injection /

Mejia, Nicholas Alexander,

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Hypersonic Stagnation Point Injection /

Record Type:	Electronic resources : Monograph/item
Title/Author:	Hypersonic Stagnation Point Injection // Nicholas Alexander Mejia.
Author:	Mejia, Nicholas Alexander,
Description:	1 electronic resource (181 pages)
Notes:	Source: Dissertations Abstracts International, Volume: 86-12, Section: B.
Contained By:	Dissertations Abstracts International86-12B.
Subject:	Physics. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=32111927
ISBN:	9798315729471

Hypersonic Stagnation Point Injection /
Mejia, Nicholas Alexander,

Hypersonic Stagnation Point Injection /Nicholas Alexander Mejia. - 1 electronic resource (181 pages)

Source: Dissertations Abstracts International, Volume: 86-12, Section: B.

Hypersonic stagnation point injection (SPI) experiments are performed using a 7◦ half-angle cone with a 19 mm radius spherical nose and a single, 1.93 mm radius sonic jet in the center of the model directed in to a Mach 6 quiet and a Mach 5.8 noisy air free stream. Injected gases include air, argon, helium, CO2, and SF6. The primary data consists of high-speed schlieren imaging at 76 kHz. Spectral analyses of the schlieren data is used to observe and define three key modes fundamental to the motions of the flow structures: (1) the longitudinal mode, (2) the vortex-coupled mode, and (3) the vortex-shedding mode. The proper orthogonal decomposition (POD) is used to track the mode energy fractions as a function of thrust coefficient while the dynamic mode decomposition (DMD) is used to gain insight into the nature of the motions present in each mode. The spectral proper orthogonal decomposition (SPOD) is used to probe specific frequencies present in the jet reservoir pressure and other spectra. As the thrust coefficient increases, the longitudinal mode becomes the dominant visible motion and the highest energy POD mode while the vortex-coupled mode becomes less energetic. The wavenumber of the Kelvin-Helmholtz instability (KHI) along the contact surface is shown to increase with thrust coefficient and under noisy flow conditions, and is shown to depend on the molar mass and speed of sound of the injected gas. This work provides the first hypersonic SPI experimental data and analyses on how different modes evolve with varying thrust coefficient and injected gas and the first observations and characterization of the KHI in an SPI flow.

English

ISBN: 9798315729471Subjects--Topical Terms:

516296
Physics.
Subjects--Index Terms:

Hypersonic stagnation point injection

Hypersonic Stagnation Point Injection /
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245 1 0 $a Hypersonic Stagnation Point Injection / $c Nicholas Alexander Mejia.
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300 $a 1 electronic resource (181 pages)
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500 $a Source: Dissertations Abstracts International, Volume: 86-12, Section: B.
500 $a Advisors: Schmidt, Bryan Committee members: Strychalski, Wanda; Hostler, Stephen; Barnhart, Paul.
502 $b Ph.D. $c Case Western Reserve University $d 2025.
520 $a Hypersonic stagnation point injection (SPI) experiments are performed using a 7◦ half-angle cone with a 19 mm radius spherical nose and a single, 1.93 mm radius sonic jet in the center of the model directed in to a Mach 6 quiet and a Mach 5.8 noisy air free stream. Injected gases include air, argon, helium, CO2, and SF6. The primary data consists of high-speed schlieren imaging at 76 kHz. Spectral analyses of the schlieren data is used to observe and define three key modes fundamental to the motions of the flow structures: (1) the longitudinal mode, (2) the vortex-coupled mode, and (3) the vortex-shedding mode. The proper orthogonal decomposition (POD) is used to track the mode energy fractions as a function of thrust coefficient while the dynamic mode decomposition (DMD) is used to gain insight into the nature of the motions present in each mode. The spectral proper orthogonal decomposition (SPOD) is used to probe specific frequencies present in the jet reservoir pressure and other spectra. As the thrust coefficient increases, the longitudinal mode becomes the dominant visible motion and the highest energy POD mode while the vortex-coupled mode becomes less energetic. The wavenumber of the Kelvin-Helmholtz instability (KHI) along the contact surface is shown to increase with thrust coefficient and under noisy flow conditions, and is shown to depend on the molar mass and speed of sound of the injected gas. This work provides the first hypersonic SPI experimental data and analyses on how different modes evolve with varying thrust coefficient and injected gas and the first observations and characterization of the KHI in an SPI flow.
546 $a English
590 $a School code: 0042
650 4 $a Physics. $3 516296
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Energy. $3 876794
650 4 $a Fluid mechanics. $3 528155
653 $a Hypersonic stagnation point injection
653 $a Flow visualization
653 $a Proper orthogonal decomposition
653 $a Spectral proper orthogonal decomposition
653 $a Dynamic mode decomposition
653 $a Supersonic retropropulsion
690 $a 0538
690 $a 0605
690 $a 0204
690 $a 0791
710 2 $a Case Western Reserve University. $b EMC - Aerospace Engineering. $e degree granting institution. $3 3815663
720 1 $a Schmidt, Bryan $e degree supervisor.
773 0 $t Dissertations Abstracts International $g 86-12B.
790 $a 0042
791 $a Ph.D.
792 $a 2025
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=32111927