Supersonic Engine Inlet - Revision history

Schuetz2 at 05:40, 17 June 2025

2025-06-17T05:40:13Z

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	title = {Supersonic Engine Inlet},		title = {Supersonic Engine Inlet},
	howpublished = {hosted at {MORwiki} -- Model Order Reduction Wiki},		howpublished = {hosted at {MORwiki} -- Model Order Reduction Wiki},
	url = <nowiki>{~~http~~://modelreduction.org/~~index.php~~/Supersonic_Engine_Inlet}</nowiki>,		url = <nowiki>{https://modelreduction.org/morwiki/Supersonic_Engine_Inlet}</nowiki>,
	year = 2005		year = 2005
	}		}

Malhotra: infobox string

2023-11-30T09:42:04Z

infobox string

@@ Line 7: / Line 7: @@
 [[Category:MIMO]]
 [[Category:Sparse]]
 ==Description: Active Control of a Supersonic Engine Inlet==

Himpe at 12:56, 25 August 2022

2022-08-25T12:56:27Z

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	[[Category:benchmark]]		[[Category:benchmark]]
	[[Category:Oberwolfach]]		[[Category:Oberwolfach]]
	[[Category:~~DAE order unspecified~~]]		[[Category:Differential_algebraic_system]]
	[[Category:linear]]		[[Category:linear]]
	[[Category:time invariant]]		[[Category:time invariant]]

Mitchell: hyphen needed

2022-03-15T12:00:15Z

hyphen needed

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	===Linearized CFD Matrices===		===Linearized CFD Matrices===

	The two-dimensional integral Euler equations are linearized about the ~~steadystate~~ solution to obtain an unsteady system of the form		The two-dimensional integral Euler equations are linearized about the steady-state solution to obtain an unsteady system of the form

	:<math>		:<math>

Saak: /* Data */

2021-12-14T09:03:01Z

Data

← Older revision		Revision as of 09:03, 14 December 2021
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	The matrices of this benchmark can be downloaded in the [http://math.nist.gov/MatrixMarket/ Matrix Market] format:		The matrices of this benchmark can be downloaded in the [http://math.nist.gov/MatrixMarket/ Matrix Market] format:
	* [http://~~www2~~.mpi-magdeburg.mpg.de/mpcsc/MORWIKI/Oberwolfach/SupersonicEngineInlet-dim1e4-Inlet.tar.gz SupersonicEngineInlet-dim1e4-Inlet.tar.gz].		* [http://csc.mpi-magdeburg.mpg.de/mpcsc/MORWIKI/Oberwolfach/SupersonicEngineInlet-dim1e4-Inlet.tar.gz SupersonicEngineInlet-dim1e4-Inlet.tar.gz].
	The size of the file is 5.4 MB.		The size of the file is 5.4 MB.
	The matrix name is used as an extension of the matrix file.		The matrix name is used as an extension of the matrix file.

Himpe: Fix CrossRefs

2021-08-27T07:58:01Z

Fix CrossRefs

Himpe: minor changes.

2018-07-31T08:23:09Z

minor changes.

← Older revision		Revision as of 08:23, 31 July 2018
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	is 2.2.</caption>]]</figure>		is 2.2.</caption>]]</figure>

	This example considers unsteady flow through a supersonic diffuser as shown in <xr id="fig1"/>.		This example considers unsteady flow through a [[wikipedia:Diffuser_(thermodynamics)#Supersonic_Diffusers\|supersonic diffuser]] as shown in <xr id="fig1"/>.
	The diffuser operates at a nominal [[wikipedia:Mach_number\|Mach number]] of <math>2.2</math>, however it is subject to perturbations in the incoming flow, which may be due (for		The diffuser operates at a nominal [[wikipedia:Mach_number\|Mach number]] of <math>2.2</math>, however it is subject to perturbations in the incoming flow, which may be due (for
	example) to atmospheric variations.		example) to atmospheric variations.
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	This control may be effected through flow bleeding upstream of the diffuser throat.		This control may be effected through flow bleeding upstream of the diffuser throat.

	A complete description of the benchmark and some model reduction results can be downloaded as PDF file [https://~~portal~~.~~uni~~-~~freiburg~~.de/~~imteksimulation/downloads/benchmark~~/~~Supersonic%20Engine%20Inlet%20%2838866%29~~/~~files~~/~~fileinnercontentproxy.2010-01-31~~.~~5794999947~~ here].		A complete description of the benchmark and some model reduction results can be downloaded as PDF file [https://www.mpi-magdeburg.mpg.de/mpcsc/MORWIKI/Oberwolfach/SupersonicEngineInlet.pdf here].

	===Active Flow Control Setup===		===Active Flow Control Setup===

Himpe: Update benchmark data file links

2018-07-17T10:58:51Z

Update benchmark data file links

← Older revision		Revision as of 10:58, 17 July 2018
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	The matrices of this benchmark can be downloaded in the [http://math.nist.gov/MatrixMarket/ Matrix Market] format:		The matrices of this benchmark can be downloaded in the [http://math.nist.gov/MatrixMarket/ Matrix Market] format:
	* [~~https~~://~~portal~~.~~uni~~-~~freiburg~~.de/~~imteksimulation~~/~~downloads~~/~~benchmark~~/~~Supersonic%20Engine%20Inlet%20%2838866%29/files/fileinnercontentproxy~~.~~2010~~-01-~~31.5849953094 inlet~~.tar.gz].		* [http://www2.mpi-magdeburg.mpg.de/mpcsc/MORWIKI/Oberwolfach/SupersonicEngineInlet-dim1e4-Inlet.tar.gz SupersonicEngineInlet-dim1e4-Inlet.tar.gz].
	The size of the file is 5.4 MB.		The size of the file is 5.4 MB.
	The matrix name is used as an extension of the matrix file.		The matrix name is used as an extension of the matrix file.
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	<ref name="korvink2005"> J.G. Korvink, E.B. Rudnyi, <span class="plainlinks">[https://doi.org/10.1007/3-540-27909-1_11 Oberwolfach Benchmark Collection]</span>, Dimension Reduction of Large-Scale Systems, Lecture Notes in Computational Science and Engineering, vol 45: 311--315, 2005.</ref>		<ref name="korvink2005"> J.G. Korvink, E.B. Rudnyi, <span class="plainlinks">[https://doi.org/10.1007/3-540-27909-1_11 Oberwolfach Benchmark Collection]</span>, Dimension Reduction of Large-Scale Systems, Lecture Notes in Computational Science and Engineering, vol 45: 311--315, 2005.</ref>

	<ref name="lassaux2002">G. Lassaux. <span class="plainlinks">[http://~~web~~.~~mit~~.~~edu~~/~~kwillcox/Public/Web~~/~~LassauxMS.pdf~~ High-Fidelity Reduced-Order Aerodynamic Models: Application to Active Control of Engine Inlets]</span>. Master’s thesis, Dept. of Aeronautics and Astronautics, MIT, June 2002.</ref>		<ref name="lassaux2002">G. Lassaux. <span class="plainlinks">[http://hdl.handle.net/1721.1/82238 High-Fidelity Reduced-Order Aerodynamic Models: Application to Active Control of Engine Inlets]</span>. Master’s thesis, Dept. of Aeronautics and Astronautics, MIT, June 2002.</ref>

	<ref name="willcox2005">K. Willcox , G. Lassaux, <span class="plainlinks">[https://doi.org/10.1007/3-540-27909-1_20 Model Reduction of an Actively Controlled Supersonic Diffuser]</span>. In: Dimension Reduction of Large-Scale Systems, Lecture Notes in Computational Science and Engineering, vol 45: 357--361, 2005.</ref>		<ref name="willcox2005">K. Willcox , G. Lassaux, <span class="plainlinks">[https://doi.org/10.1007/3-540-27909-1_20 Model Reduction of an Actively Controlled Supersonic Diffuser]</span>. In: Dimension Reduction of Large-Scale Systems, Lecture Notes in Computational Science and Engineering, vol 45: 357--361, 2005.</ref>

	</references>		</references>

Himpe: Minor fixes.

2018-05-14T14:14:45Z

Minor fixes.

← Older revision		Revision as of 14:14, 14 May 2018
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	~~{{preliminary}} <!-- Do not remove -->~~

	[[Category:benchmark]]		[[Category:benchmark]]
	[[Category:Oberwolfach]]		[[Category:Oberwolfach]]
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	This example considers unsteady flow through a supersonic diffuser as shown in <xr id="fig1"/>.		This example considers unsteady flow through a supersonic diffuser as shown in <xr id="fig1"/>.
	The diffuser operates at a nominal Mach number of 2.2, however it is subject to perturbations in the incoming flow, which may be due (for		The diffuser operates at a nominal [[wikipedia:Mach_number\|Mach number]] of <math>2.2</math>, however it is subject to perturbations in the incoming flow, which may be due (for
	example) to atmospheric variations.		example) to atmospheric variations.
	In nominal operation, there is a strong shock downstream of the diffuser throat, as can be seen from the Mach contours		In nominal operation, there is a strong shock downstream of the diffuser throat, as can be seen from the Mach contours
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	The unknown flow quantities used are the density, streamwise velocity component, normal velocity component, and enthalpy at each point in the computational grid.		The unknown flow quantities used are the density, streamwise velocity component, normal velocity component, and enthalpy at each point in the computational grid.
	Note that the local flow velocity components <math>q</math> and <math>q^{\perp}</math> are defined using a streamline computational grid that is computed for the steady-state solution.		Note that the local flow velocity components <math>q</math> and <math>q^{\perp}</math> are defined using a streamline computational grid that is computed for the steady-state solution.
	<math>q</math> is the projection of the flow velocity on the meanline direction of the grid cell, and <math>q^{\perp}</math> is the ~~normalto~~-meanline component.		<math>q</math> is the projection of the flow velocity on the meanline direction of the grid cell, and <math>q^{\perp}</math> is the normal-to-meanline component.
	To simplify the implementation of the integral energy equation, total enthalpy is also used in place of energy.		To simplify the implementation of the integral energy equation, total enthalpy is also used in place of energy.
	The vector of unknowns at each node <math>i</math> is therefore		The vector of unknowns at each node <math>i</math> is therefore

Werner: Added link in references.

2018-04-25T12:45:35Z

Added link in references.

← Older revision		Revision as of 12:45, 25 April 2018
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	<ref name="korvink2005"> J.G. Korvink, E.B. Rudnyi, <span class="plainlinks">[https://doi.org/10.1007/3-540-27909-1_11 Oberwolfach Benchmark Collection]</span>, Dimension Reduction of Large-Scale Systems, Lecture Notes in Computational Science and Engineering, vol 45: 311--315, 2005.</ref>		<ref name="korvink2005"> J.G. Korvink, E.B. Rudnyi, <span class="plainlinks">[https://doi.org/10.1007/3-540-27909-1_11 Oberwolfach Benchmark Collection]</span>, Dimension Reduction of Large-Scale Systems, Lecture Notes in Computational Science and Engineering, vol 45: 311--315, 2005.</ref>

	<ref name="lassaux2002">G. Lassaux. High-Fidelity Reduced-Order Aerodynamic Models: Application to Active Control of Engine Inlets. Master’s thesis, Dept. of Aeronautics and Astronautics, MIT, June 2002.</ref>		<ref name="lassaux2002">G. Lassaux. <span class="plainlinks">[http://web.mit.edu/kwillcox/Public/Web/LassauxMS.pdf High-Fidelity Reduced-Order Aerodynamic Models: Application to Active Control of Engine Inlets]</span>. Master’s thesis, Dept. of Aeronautics and Astronautics, MIT, June 2002.</ref>

	<ref name="willcox2005">K. Willcox , G. Lassaux, <span class="plainlinks">[https://doi.org/10.1007/3-540-27909-1_20 Model Reduction of an Actively Controlled Supersonic Diffuser]</span>. In: Dimension Reduction of Large-Scale Systems, Lecture Notes in Computational Science and Engineering, vol 45: 357--361, 2005.</ref>		<ref name="willcox2005">K. Willcox , G. Lassaux, <span class="plainlinks">[https://doi.org/10.1007/3-540-27909-1_20 Model Reduction of an Actively Controlled Supersonic Diffuser]</span>. In: Dimension Reduction of Large-Scale Systems, Lecture Notes in Computational Science and Engineering, vol 45: 357--361, 2005.</ref>

	</references>		</references>

← Older revision		Revision as of 07:58, 27 August 2021
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	is 2.2.</caption>]]</figure>		is 2.2.</caption>]]</figure>

	This example considers unsteady flow through a [[wikipedia:Diffuser_(thermodynamics)#Supersonic_Diffusers\|supersonic diffuser]] as shown in ~~<xr id="fig1"/>~~.		This example considers unsteady flow through a [[wikipedia:Diffuser_(thermodynamics)#Supersonic_Diffusers\|supersonic diffuser]] as shown in Fig. 1.
	The diffuser operates at a nominal [[wikipedia:Mach_number\|Mach number]] of <math>2.2</math>, however it is subject to perturbations in the incoming flow, which may be due (for		The diffuser operates at a nominal [[wikipedia:Mach_number\|Mach number]] of <math>2.2</math>, however it is subject to perturbations in the incoming flow, which may be due (for
	example) to atmospheric variations.		example) to atmospheric variations.
	In nominal operation, there is a strong shock downstream of the diffuser throat, as can be seen from the Mach contours		In nominal operation, there is a strong shock downstream of the diffuser throat, as can be seen from the Mach contours
	plotted in Figure ~~<xr id="fig1"/>~~.		plotted in Figure Fig. 1.
	Incoming disturbances can cause the shock to move forward towards the throat. When the shock sits at the throat, the inlet		Incoming disturbances can cause the shock to move forward towards the throat. When the shock sits at the throat, the inlet
	is unstable, since any disturbance that moves the shock slightly upstream will cause it to move forward rapidly, leading to unstart of the inlet. This is extremely undesirable, since unstart results in a large loss of thrust.		is unstable, since any disturbance that moves the shock slightly upstream will cause it to move forward rapidly, leading to unstart of the inlet. This is extremely undesirable, since unstart results in a large loss of thrust.
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	<figure id="fig2">[[File:Supersonic_Inlet2.png\|600px\|thumb\|right\|<caption>Supersonic diffuser active flow control problem setup.</caption>]]</figure>		<figure id="fig2">[[File:Supersonic_Inlet2.png\|600px\|thumb\|right\|<caption>Supersonic diffuser active flow control problem setup.</caption>]]</figure>

	~~<xr id="fig2"/>~~ presents the schematic of the actuation mechanism.		Fig. 2 presents the schematic of the actuation mechanism.
	Incoming flow with possible disturbances enters the inlet and is sensed using pressure sensors.		Incoming flow with possible disturbances enters the inlet and is sensed using pressure sensors.
	The controller then adjusts the bleed upstream of the throat in order to control the position of the shock and to prevent it from moving upstream.		The controller then adjusts the bleed upstream of the throat in order to control the position of the shock and to prevent it from moving upstream.