Abstract
Aerodynamic research on Mars for the past few decades has increased in the development of optimum aerial vehicles for Mars. The current research aims to study the aerodynamics of a triangular airfoil in Mars atmospheric conditions and understand the future regions of flow improvement. A numerical investigation using a Finite Volume Solver has been performed for 0° to 16° angles of attack at low and high flow velocities. Low flow velocities ranging from Re = 3,000 to 7,000 have been considered for the investigation. The nonlinearity in Cl appears as the separation bubble begins to approach the apex on the suction surface. Apart from the separation bubble, a flow recirculation zone is generated for low and high Re. at α = 16°. The highest aerodynamic performance is at α = 6°.
| Original language | English |
|---|---|
| Article number | https://doi.org/10.1080/10407782.2024.2353350 |
| Number of pages | 21 |
| Journal | Numerical Heat Transfer Part A: Applications: an international journal of computation and methodology |
| DOIs | |
| Publication status | Published - 2024 |
| Externally published | Yes |
Bibliographical note
Green Open Access added to TU Delft Institutional Repository ‘You share, we take care!’ – Taverne project https://www.openaccess.nl/en/you-share-we-take-careOtherwise as indicated in the copyright section: the publisher is the copyright holder of this work and the author uses the Dutch legislation to make this work public.