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Control surface hinge moment predict...

ProQuest Information and Learning Co.

Control surface hinge moment prediction using computational fluid dynamics.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Control surface hinge moment prediction using computational fluid dynamics./
Author:	Simpson, Christopher David.
Description:	1 online resource (143 pages)
Notes:	Source: Masters Abstracts International, Volume: 56-01.
Contained By:	Masters Abstracts International56-01(E).
Subject:	Aerospace engineering. -
Online resource:	click for full text (PQDT)
ISBN:	9781369175028

Control surface hinge moment prediction using computational fluid dynamics.
Simpson, Christopher David.

Control surface hinge moment prediction using computational fluid dynamics. - 1 online resource (143 pages)

Source: Masters Abstracts International, Volume: 56-01.

Thesis (M.S.)

Includes bibliographical references

The following research determines the feasibility of predicting control surface hinge moments using various computational methods. A detailed analysis is conducted using a 2D GA(W)-1 airfoil with a 20% plain flap. Simple hinge moment prediction methods are tested, including empirical Datcom relations and XFOIL. Steady-state and time-accurate turbulent, viscous, Navier-Stokes solutions are computed using Fun3D. Hinge moment coefficients are computed. Mesh construction techniques are discussed. An adjoint-based mesh adaptation case is also evaluated. An NACA 0012 45-degree swept horizontal stabilizer with a 25% elevator is also evaluated using Fun3D. Results are compared with experimental wind-tunnel data obtained from references. Finally, the costs of various solution methods are estimated.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2018

Mode of access: World Wide Web

ISBN: 9781369175028Subjects--Topical Terms:

686400
Aerospace engineering.
Index Terms--Genre/Form:

554714
Electronic books.

Control surface hinge moment prediction using computational fluid dynamics.
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006 m o u
007 cr mn||||a|a||
008 190606s2016 xx obm 000 0 eng d
020 $a 9781369175028
035 $a (MiAaPQ)AAI10162714
035 $a (MiAaPQ)alatus:12855
035 $a AAI10162714
040 $a MiAaPQ $b eng $c MiAaPQ
099 $a TUL $f hyy $c available through World Wide Web
100 1 $a Simpson, Christopher David. $3 1180305
245 1 0 $a Control surface hinge moment prediction using computational fluid dynamics.
264 0 $c 2016
300 $a 1 online resource (143 pages)
336 $a text $b txt $2 rdacontent
337 $a computer $b c $2 rdamedia
338 $a online resource $b cr $2 rdacarrier
500 $a Source: Masters Abstracts International, Volume: 56-01.
500 $a Adviser: Charles R. O'Neill.
502 $a Thesis (M.S.) $c The University of Alabama $d 2016.
504 $a Includes bibliographical references
520 $a The following research determines the feasibility of predicting control surface hinge moments using various computational methods. A detailed analysis is conducted using a 2D GA(W)-1 airfoil with a 20% plain flap. Simple hinge moment prediction methods are tested, including empirical Datcom relations and XFOIL. Steady-state and time-accurate turbulent, viscous, Navier-Stokes solutions are computed using Fun3D. Hinge moment coefficients are computed. Mesh construction techniques are discussed. An adjoint-based mesh adaptation case is also evaluated. An NACA 0012 45-degree swept horizontal stabilizer with a 25% elevator is also evaluated using Fun3D. Results are compared with experimental wind-tunnel data obtained from references. Finally, the costs of various solution methods are estimated.
520 $a Results indicate that while a steady-state Navier-Stokes solution can accurately predict control surface hinge moments for small angles of attack and deflection angles, a time-accurate solution is necessary to accurately predict hinge moments in the presence of flow separation. The ability to capture the unsteady vortex shedding behavior present in moderate to large control surface deflections is found to be critical to hinge moment prediction accuracy. Adjoint-based mesh adaptation is shown to give hinge moment predictions similar to a globally-refined mesh for a steady-state 2D simulation.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2018
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 686400
655 7 $a Electronic books. $2 local $3 554714
690 $a 0538
710 2 $a ProQuest Information and Learning Co. $3 1178819
710 2 $a The University of Alabama. $b Aerospace Engineering. $3 845697
773 0 $t Masters Abstracts International $g 56-01(E).
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10162714 $z click for full text (PQDT)

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