NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWS
Aerodynamic performance of a two-element camber morphing airfoil was investigated at low Reynolds number using the transient SST model in ANSYS FLUENT 14.0 and eN method in XFLR5. The two-element camber morphing concept was employed to morph the baseline airfoil into another airfoil by altering the...
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| Format: | Article |
| Language: | English |
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Taylor's University
2017-07-01
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| Series: | Journal of Engineering Science and Technology |
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| Online Access: | http://jestec.taylors.edu.my/Vol%2012%20issue%207%20July%202017/12_7_17.pdf |
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| author | RAJESH SENTHIL KUMAR T. V. SIVAKUMAR BALAJEE RAMAKRISHNANANDA ARJHUN A.K, SURIYAPANDIYAN |
| author_facet | RAJESH SENTHIL KUMAR T. V. SIVAKUMAR BALAJEE RAMAKRISHNANANDA ARJHUN A.K, SURIYAPANDIYAN |
| author_sort | RAJESH SENTHIL KUMAR T. |
| collection | DOAJ |
| description | Aerodynamic performance of a two-element camber morphing airfoil was investigated at low Reynolds number using the transient SST model in ANSYS FLUENT 14.0 and eN method in XFLR5. The two-element camber morphing concept was employed to morph the baseline airfoil into another airfoil by altering the orientation of mean-line at 35% of the chord to achieve better aerodynamic efficiency. NACA 0012 was selected as baseline airfoil. NACA 23012 was chosen as the test case as it has the camber-line similar to that of the morphed airfoil and as it has the same thickness as that of the baseline airfoil. The simulations were carried out at chord based Reynolds numbers of 2.5×105
and 3.9×105. The aerodynamic force coefficients, aerodynamic efficiency and the location of the transition point of laminar separation bubble over these airfoils were studied for various angles of attack. It was found that the aerodynamic efficiency of the morphed airfoil was 12% higher than that of the target airfoil at
4° angle of attack for Reynolds number of 3.9×105 and 54% rise in aerodynamic performance was noted as Reynolds number was varied from 2.5×105 to 3.9×105. The morphed airfoil exhibited the nature of low Reynolds number airfoil. |
| first_indexed | 2024-12-12T11:48:41Z |
| format | Article |
| id | doaj.art-35df80612c3846ddbac2ae8b5e195108 |
| institution | Directory Open Access Journal |
| issn | 1823-4690 |
| language | English |
| last_indexed | 2024-12-12T11:48:41Z |
| publishDate | 2017-07-01 |
| publisher | Taylor's University |
| record_format | Article |
| series | Journal of Engineering Science and Technology |
| spelling | doaj.art-35df80612c3846ddbac2ae8b5e1951082022-12-22T00:25:22ZengTaylor's UniversityJournal of Engineering Science and Technology1823-46902017-07-0112719391955NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWSRAJESH SENTHIL KUMAR T.0V. SIVAKUMAR1BALAJEE RAMAKRISHNANANDA2ARJHUN A.K, SURIYAPANDIYAN3Department of Aerospace Engineering, Amrita School of Engineering Coimbatore, Amrita Vishwa Vidyapeetham, Amrita University,641112, Tamil Nadu, IndiaDepartment of Aerospace Engineering, Amrita School of Engineering Coimbatore, Amrita Vishwa Vidyapeetham, Amrita University,641112, Tamil Nadu, IndiaDepartment of Aerospace Engineering, Amrita School of Engineering Coimbatore, Amrita Vishwa Vidyapeetham, Amrita University,641112, Tamil Nadu, IndiaDepartment of Aerospace Engineering, Amrita School of Engineering Coimbatore, Amrita Vishwa Vidyapeetham, Amrita University,641112, Tamil Nadu, IndiaAerodynamic performance of a two-element camber morphing airfoil was investigated at low Reynolds number using the transient SST model in ANSYS FLUENT 14.0 and eN method in XFLR5. The two-element camber morphing concept was employed to morph the baseline airfoil into another airfoil by altering the orientation of mean-line at 35% of the chord to achieve better aerodynamic efficiency. NACA 0012 was selected as baseline airfoil. NACA 23012 was chosen as the test case as it has the camber-line similar to that of the morphed airfoil and as it has the same thickness as that of the baseline airfoil. The simulations were carried out at chord based Reynolds numbers of 2.5×105 and 3.9×105. The aerodynamic force coefficients, aerodynamic efficiency and the location of the transition point of laminar separation bubble over these airfoils were studied for various angles of attack. It was found that the aerodynamic efficiency of the morphed airfoil was 12% higher than that of the target airfoil at 4° angle of attack for Reynolds number of 3.9×105 and 54% rise in aerodynamic performance was noted as Reynolds number was varied from 2.5×105 to 3.9×105. The morphed airfoil exhibited the nature of low Reynolds number airfoil.http://jestec.taylors.edu.my/Vol%2012%20issue%207%20July%202017/12_7_17.pdfMorphing airfoilSUAVCFDLow Reynolds number flow; Aerodynamics.Low Reynolds number flowAerodynamics |
| spellingShingle | RAJESH SENTHIL KUMAR T. V. SIVAKUMAR BALAJEE RAMAKRISHNANANDA ARJHUN A.K, SURIYAPANDIYAN NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWS Journal of Engineering Science and Technology Morphing airfoil SUAV CFD Low Reynolds number flow; Aerodynamics. Low Reynolds number flow Aerodynamics |
| title | NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWS |
| title_full | NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWS |
| title_fullStr | NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWS |
| title_full_unstemmed | NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWS |
| title_short | NUMERICAL INVESTIGATION OF TWO ELEMENT CAMBER MORPHING AIRFOIL IN LOW REYNOLDS NUMBER FLOWS |
| title_sort | numerical investigation of two element camber morphing airfoil in low reynolds number flows |
| topic | Morphing airfoil SUAV CFD Low Reynolds number flow; Aerodynamics. Low Reynolds number flow Aerodynamics |
| url | http://jestec.taylors.edu.my/Vol%2012%20issue%207%20July%202017/12_7_17.pdf |
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