A study of the reverse delta wing using particle image velocimetry (PIV) /
Particle Image Velocimetry was used in a low speed wind tunnel to investigate the vortex structures of a slender reverse delta wing at various angles of attack and roll. This work investigates the characteristics of the vortices generated downstream in planes perpendicular to the free stream directi...
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| Main Author: | |
|---|---|
| Format: | Thesis |
| Language: | English |
| Published: |
Gombak, Selangor :
Kulliyyah of Engineering, International Islamic University Malaysia,
2011
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| Subjects: | |
| Online Access: | http://studentrepo.iium.edu.my/handle/123456789/4848 |
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|---|---|---|---|
| 008 | 110606t2011 my a g m 000 0 eng d | ||
| 040 | |a UIAM |b eng | ||
| 041 | |a eng | ||
| 050 | 0 | 0 | |a TL673.T7 |
| 100 | 1 | |a Altaf, Afaq | |
| 245 | 1 | 2 | |a A study of the reverse delta wing using particle image velocimetry (PIV) / |c by Afaq Altaf |
| 260 | |a Gombak, Selangor : |b Kulliyyah of Engineering, International Islamic University Malaysia, |c 2011 | ||
| 300 | |a xviii, 106 leaves : |b ill. ; |c 30cm. | ||
| 500 | |a Abstracts in English and Arabic. | ||
| 500 | |a "A thesis submitted in fulfilment of the requirement for the degree of Master of Science (Mechanical Engineering)."--On t.p. | ||
| 502 | |a Thesis (MSME)--International Islamic University Malaysia, 2011. | ||
| 504 | |a Includes bibliographical references (leaves 97-99). | ||
| 520 | |a Particle Image Velocimetry was used in a low speed wind tunnel to investigate the vortex structures of a slender reverse delta wing at various angles of attack and roll. This work investigates the characteristics of the vortices generated downstream in planes perpendicular to the free stream direction and their dependence on angles of attack and roll at chord-based Reynolds number of Rec=3.82×105. The peak tangential velocities show a trend similar to a delta wing. A six component force balance was used to obtain the aerodynamic coefficients for a reverse delta wing and a delta wing. A qualitative comparison with existing computational results is executed for velocity vectors and surface pressure contours; whereby the computational results of surface pressure contours agree with the six component force balance results, revealing that a regular delta wing exhibits a higher CL than a reverse delta wing. It can be concluded that a regular delta wing vortex at a particular angle of attack exhibits a tangential velocity magnitude twice that of a reverse delta wing; exhibits higher circulation and vorticity than a reverse delta wing vortex. | ||
| 596 | |a 1 | ||
| 650 | 0 | 0 | |a Airplanes |x Wings, Triangular |
| 650 | 0 | 0 | |a Particle image velocimetry |
| 655 | 7 | |a Theses, IIUM local | |
| 690 | |a Dissertations, Academic |x Department of Mechanical Engineering |z IIUM | ||
| 710 | 2 | |a International Islamic University Malaysia. |b Department of Mechanical Engineering | |
| 856 | 4 | |u http://studentrepo.iium.edu.my/handle/123456789/4848 | |
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