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Aerodynamic testing and analysis of ...
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Horton, Amanda Neely.
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Aerodynamic testing and analysis of offset planar wings and opposing offset tails.
紀錄類型:
書目-語言資料,印刷品 : Monograph/item
正題名/作者:
Aerodynamic testing and analysis of offset planar wings and opposing offset tails./
作者:
Horton, Amanda Neely.
面頁冊數:
66 p.
附註:
Adviser: D. Brian Landrum.
Contained By:
Masters Abstracts International45-04.
標題:
Engineering, Aerospace. -
電子資源:
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.
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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.
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