Optimal Aft End Distorted Fin Model Using Response Surface Method

Cited 1 time in webofscience Cited 0 time in scopus
  • Hit : 267
  • Download : 0
In wind-tunnel testing of bomb or missile-type models, aft end geometry distortion may become necessary when a model is tested by using a sting support system. When the diameter of the model base is increased, the exposed tail fin area is reduced to result in aerodynamic data alteration. In the present work, various tests are conducted on an MK-82 bomb model with base diameter and exposed tail fin area variations. The tests use techniques involving design of experiments and response surface modeling. The effects of the model base geometry modifications on the aerodynamic characteristics are investigated. Experimental design optimization is then performed on the basis of three design factors: the base diameter, the extended tail fin area, and the freestream velocity. The experimental results show that the altered aerodynamic characteristics due to aft end model distortion can be minimized by changing the tail fin geometry on the basis of the regression model.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
2009-05
Language
English
Article Type
Article
Citation

JOURNAL OF SPACECRAFT AND ROCKETS, v.46, no.3, pp.592 - 598

ISSN
0022-4650
DOI
10.2514/1.40496
URI
http://hdl.handle.net/10203/99549
Appears in Collection
AE-Journal Papers(저널논문)
Files in This Item
There are no files associated with this item.
This item is cited by other documents in WoS
⊙ Detail Information in WoSⓡ Click to see webofscience_button
⊙ Cited 1 items in WoS Click to see citing articles in records_button

qr_code

  • mendeley

    citeulike


rss_1.0 rss_2.0 atom_1.0