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Aerodynamic testing and analysis of ...

Horton, Amanda Neely.

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Aerodynamic testing and analysis of offset planar wings and opposing offset tails.

Record Type:	Language materials, printed : Monograph/item
Title/Author:	Aerodynamic testing and analysis of offset planar wings and opposing offset tails./
Author:	Horton, Amanda Neely.
Description:	66 p.
Notes:	Adviser: D. Brian Landrum.
Contained By:	Masters Abstracts International45-04.
Subject:	Engineering, Aerospace. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=1441945

Aerodynamic testing and analysis of offset planar wings and opposing offset tails.
Horton, Amanda Neely.

Aerodynamic testing and analysis of offset planar wings and opposing offset tails. - 66 p.

Adviser: D. Brian Landrum.

Thesis (M.S.)--The University of Alabama in Huntsville, 2007.

The experimental aerodynamics of an unconventional missile configuration are presented as a function of angle of attack for subsonic, transonic, and supersonic Mach numbers. The configuration consists of an elliptic body with a pair of offset-mounted, large area wings. Tail surfaces are positioned in the same offset horizontal planes as the wings but are deployed on opposite sides of the body. Wind tunnel test results show that the offset body-wing-tail configuration produces significant side forces and rolling moments at angle of attack. Aerodynamic predictions from the engineering-level Missile DATCOM code and the ETA and GASP CFD codes are also discussed.Subjects--Topical Terms:

1018395
Engineering, Aerospace.

Aerodynamic testing and analysis of offset planar wings and opposing offset tails.
LDR:01515nam 2200265 a 45 001 974068
005 20110928
008 110928s2007 eng d
035 $a (UMI)AAI1441945
035 $a AAI1441945
040 $a UMI $c UMI
100 1 $a Horton, Amanda Neely. $3 1298007
245 1 0 $a Aerodynamic testing and analysis of offset planar wings and opposing offset tails.
300 $a 66 p.
500 $a Adviser: D. Brian Landrum.
500 $a Source: Masters Abstracts International, Volume: 45-04, page: 2018.
502 $a Thesis (M.S.)--The University of Alabama in Huntsville, 2007.
520 $a The experimental aerodynamics of an unconventional missile configuration are presented as a function of angle of attack for subsonic, transonic, and supersonic Mach numbers. The configuration consists of an elliptic body with a pair of offset-mounted, large area wings. Tail surfaces are positioned in the same offset horizontal planes as the wings but are deployed on opposite sides of the body. Wind tunnel test results show that the offset body-wing-tail configuration produces significant side forces and rolling moments at angle of attack. Aerodynamic predictions from the engineering-level Missile DATCOM code and the ETA and GASP CFD codes are also discussed.
590 $a School code: 0278.
650 4 $a Engineering, Aerospace. $3 1018395
650 4 $a Physics, Fluid and Plasma. $3 1018402
690 $a 0538
690 $a 0759
710 2 $a The University of Alabama in Huntsville. $3 1017884
773 0 $t Masters Abstracts International $g 45-04.
790 $a 0278
790 1 0 $a Landrum, D. Brian, $e advisor
791 $a M.S.
792 $a 2007
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=1441945