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| Content Provider | Springer Nature Link |
|---|---|
| Author | Mohammadi, Morteza Taleghani, A. Shams |
| Copyright Year | 2013 |
| Abstract | Active flow control has great importance in design of flying objects in general and control flaps in particular. Using dielectric barrier discharge as plasma actuators over control flaps can cause a change in position of separation point or can eliminate it. The present study aims to investigate experimentally the effects of the plasma actuator over a NACA0012 airfoil in high angles of attack up to 6° above the stall in order to displace the separation point. Therefore the effects of the plasma actuator with unsteady sine wave excitation and different duty cycles on airfoil pressure coefficient distribution and lift coefficient are studied. The experiments were performed at Re $_{ c }$ = 3.7 × 10$^{5}$. The results indicate that lift coefficient increases with unsteady plasma actuation at post-stall angles of attack up to 6°. The improvement of the pressure coefficient distribution in upper side of airfoil for lower duty cycles of about 14 % was shown to be better than higher duty cycles of above 50 %. |
| Starting Page | 2363 |
| Ending Page | 2370 |
| Page Count | 8 |
| File Format | |
| ISSN | 13198025 |
| Journal | Arabian Journal for Science and Engineering |
| Volume Number | 39 |
| Issue Number | 3 |
| e-ISSN | 21914281 |
| Language | English |
| Publisher | Springer Berlin Heidelberg |
| Publisher Date | 2013-09-08 |
| Publisher Place | Berlin, Heidelberg |
| Access Restriction | One Nation One Subscription (ONOS) |
| Subject Keyword | Plasma actuator DBD AC voltage Duty cycle Lift Airfoil Unsteady actuation Engineering Science |
| Content Type | Text |
| Resource Type | Article |
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