Wiratama, I Kade (2021) Computational Investigation Of Deploying Microtabs On Airfoil Wortmann FX63-137. Computational Investigation Of Deploying Microtabs On Airfoil Wortmann FX63-137, - (-). ---. ISSN 1816 012108
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Abstract
Flow on the airfoil with deploying microtabs was performed to investigation aerodynamic performance airfoil modified with microtabs. Computer Fluid Dynamic (CFD) simulation has already been conducted to study the effects of heights deploying tab to the aerodynamic performance characteristics of airfoil sections. The aim of this study was performed to determine the effect of tab heights under variations of angle of attack againt the behaviour of stall airfoil and determine the effect of tab heights on the lift coefficient (CL) and drag coefficient (CD) on tab heights of 1.1% C, 2,2% C and 3.3% C for upper and lower surfaces airfoil. The angle of attach airfoil was from -4o to 32o with interval 20. From the results of CFD simulations showed that the addition of microtabs on the airfoil Wortmann FX63-137 for the lower surface had the effect of increasing the lift force and lift coefficient, the increase occurred consistently and stall occurred at an angle of 26o for tab heights of 1.1% C and 2,2%C while the tab height of 3.3% C a stall occurred at an angle of 20o. For upper surface, microtabs caused a decrease in lift force and stalls occurred at angle of 22o for all tab heights. The drag coefficient also increased under the increasing angle of attack with highest value was at tab height of 1.1% C of 2.542 and an angle of attack of 280, while on the lower surface the largest drag coefficient was at a tab height of 3.3% C of 2.73.
| Item Type: | Article |
|---|---|
| Subjects: | T Technology > TJ Mechanical engineering and machinery |
| Divisions: | Fakultas Teknik |
| Depositing User: | I Kade Wiratama, ST., M.Sc.Ph.D |
| Date Deposited: | 02 Jul 2023 02:28 |
| Last Modified: | 02 Jul 2023 02:28 |
| URI: | http://eprints.unram.ac.id/id/eprint/40595 |
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