Özet
This paper studies and compares the effects of transverse and vortex gust encounters. A sine-squared transverse gust was physically created in a water-filled towing tank via a free jet, while a vortex gust was created in a water channel by placing a gust generator plate that undergoes a clockwise half-rotation upstream of the test model. Force and flow field measurements were acquired in both cases. It was found that the gust encounter results in large force transients that follow similar trends during both the transverse and vortex gust encounters. In both cases, unsteady forcing was found to have dependency on time varying effective angle of attack. In order to mitigate the gust effects on lift, different pitching maneuvers were investigated and it has been found that forces produced by a pitching motion can dominate the force produced in a gust encounter.
| Orijinal dil | İngilizce |
|---|---|
| Ana bilgisayar yayını başlığı | AIAA Scitech 2019 Forum |
| Yayınlayan | American Institute of Aeronautics and Astronautics Inc, AIAA |
| ISBN (Basılı) | 9781624105784 |
| DOI'lar | |
| Yayın durumu | Yayınlandı - 2019 |
| Etkinlik | AIAA Scitech Forum, 2019 - San Diego, United States Süre: 7 Oca 2019 → 11 Oca 2019 |
Yayın serisi
| Adı | AIAA Scitech 2019 Forum |
|---|
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| ???event.eventtypes.event.conference??? | AIAA Scitech Forum, 2019 |
|---|---|
| Ülke/Bölge | United States |
| Şehir | San Diego |
| Periyot | 7/01/19 → 11/01/19 |
Bibliyografik not
Publisher Copyright:� 2019 by German Aerospace Center (DLR). Published by the American Institute of Aeronautics and Astronautics, Inc.
Finansman
The authors (HB and ARJ) gratefully acknowledge support from the Air Force Office of Scientific Research under grant FA9550-16-1-0508. Work at ITU is supported by TUBITAK Grant 115M358 (For the Application on UAVs and MAVs, Gust Effect on the Performance of Wings in Motion (Maneuver or Flapping) and Flow Control Attempts).
| Finansörler | Finansör numarası |
|---|---|
| TUBITAK | 115M358 |
| UAVs | |
| Air Force Office of Scientific Research | FA9550-16-1-0508 |
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