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Inviscid Hypersonic Flow Past Canonical Bodies.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Inviscid Hypersonic Flow Past Canonical Bodies./
Author:	Paredes, Daniel.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2021,
Description:	50 p.
Notes:	Source: Masters Abstracts International, Volume: 83-03.
Contained By:	Masters Abstracts International83-03.
Subject:	Mechanical engineering. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28498516
ISBN:	9798535533353

Inviscid Hypersonic Flow Past Canonical Bodies.
Paredes, Daniel.

Inviscid Hypersonic Flow Past Canonical Bodies. - Ann Arbor : ProQuest Dissertations & Theses, 2021 - 50 p.

Source: Masters Abstracts International, Volume: 83-03.

Thesis (M.S.)--University of Colorado Colorado Springs, 2021.

This item must not be sold to any third party vendors.

Hypersonic flow past a conical body with a control surface is of great importance to understand what might happen on an actual flight vehicle. A slender cone with a wedge-shaped control surface is of particular interest by the Joint Computational/Experimental Aerodynamics Program (JCEAP). The aerodynamics of this specific geometry is very complex in terms of multiple shock wave interactions. As a preliminary study, therefore, inviscid hypersonic flow past a wedge or a cone was numerically investigated. An in-house solver using the WENO scheme was used to capture the complex wave structures. It was found that double Mach reflection was well captured for Mach number (M_∞) greater than 5. ANSYS Fluent was used to simulate 2D axisymmetric conical flow. It was found that Fluent can generate accurate results on drag coefficient and shock wave angle. Fluent was also used to simulate 3D conical flow at an angle of attack ranging from 0° to 20°. It was observed that at high angle of attack, Mach number independence extended to the supersonic flow regime. For example, the drag coefficient generated by a 10° half-angle cone at 15° angle of attack became Mach number independent when M_∞ is greater than 2.72.

ISBN: 9798535533353Subjects--Topical Terms:

649730
Mechanical engineering.
Subjects--Index Terms:

Canonical bodies

Inviscid Hypersonic Flow Past Canonical Bodies.
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100 1 $a Paredes, Daniel. $3 3681435
245 1 0 $a Inviscid Hypersonic Flow Past Canonical Bodies.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2021
300 $a 50 p.
500 $a Source: Masters Abstracts International, Volume: 83-03.
500 $a Advisor: Wan, Hui.
502 $a Thesis (M.S.)--University of Colorado Colorado Springs, 2021.
506 $a This item must not be sold to any third party vendors.
520 $a Hypersonic flow past a conical body with a control surface is of great importance to understand what might happen on an actual flight vehicle. A slender cone with a wedge-shaped control surface is of particular interest by the Joint Computational/Experimental Aerodynamics Program (JCEAP). The aerodynamics of this specific geometry is very complex in terms of multiple shock wave interactions. As a preliminary study, therefore, inviscid hypersonic flow past a wedge or a cone was numerically investigated. An in-house solver using the WENO scheme was used to capture the complex wave structures. It was found that double Mach reflection was well captured for Mach number (M_∞) greater than 5. ANSYS Fluent was used to simulate 2D axisymmetric conical flow. It was found that Fluent can generate accurate results on drag coefficient and shock wave angle. Fluent was also used to simulate 3D conical flow at an angle of attack ranging from 0° to 20°. It was observed that at high angle of attack, Mach number independence extended to the supersonic flow regime. For example, the drag coefficient generated by a 10° half-angle cone at 15° angle of attack became Mach number independent when M_∞ is greater than 2.72.
590 $a School code: 0892.
650 4 $a Mechanical engineering. $3 649730
650 4 $a Acoustics. $3 879105
650 4 $a Fluid mechanics. $3 528155
650 4 $a Simulation. $3 644748
650 4 $a Velocity. $3 3560495
650 4 $a Accuracy. $3 3559958
650 4 $a Viscosity. $3 1050706
650 4 $a Temperature effects. $3 3560297
650 4 $a Fluid-structure interaction. $3 907285
650 4 $a Aerodynamics. $3 532569
650 4 $a Variables. $3 3548259
650 4 $a Pressure distribution. $3 3564852
650 4 $a Heat. $3 573595
650 4 $a Energy. $3 876794
650 4 $a Reynolds number. $3 3681436
650 4 $a Boundary conditions. $3 3560411
650 4 $a Flow control. $3 3681437
650 4 $a Navier Stokes equations. $3 3681438
653 $a Canonical bodies
653 $a Hypersonic
653 $a Inviscid flow
690 $a 0548
690 $a 0204
690 $a 0986
690 $a 0791
710 2 $a University of Colorado Colorado Springs. $b College of Engineering and Applied Science-Mechanical Engineering. $3 3342934
773 0 $t Masters Abstracts International $g 83-03.
790 $a 0892
791 $a M.S.
792 $a 2021
793 $a English
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28498516