Studi CFD Aliran Udara Di Sekeliling WING NACA0015 Yang Dilengkapi Split Flap
The values of lift and drag coefficients of airfoil which is formed by Wing NACA0015 can be obtained through numerical approach, for example by using CFX. The objectives of this study are to simulate and to get the optimum angle of deflection flap and angle of attack and to describe the lift coeffic...
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| Main Authors: | , , |
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| Format: | Book |
| Published: |
2015.
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| Subjects: | |
| Online Access: | Connect to this object online |
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