Set up your own cloud-native simulation in minutes.Start Simulating Now
1 Geometry
1 Mesh
1 Simulation setup
1 ResultWhat is the project goal: Aerodynamic performance evaluation of the primary rotor blade (NACA 64-210 baseline, root-to-tip taper) for a solar-powered tilt-rotor eVTOL, across hover and cruise operating conditions. This blade forms part of the Sthiratej platform, a Low-Altitude eVTOL under development for coastal dark-vessel and IUU fishing surveillance. Simulation type: Steady-state RANS (SST k-ω, transition-enabled) for 2D/3D airfoil polar sweep across angle of attack, at two Reynolds number regimes corresponding to hover (low advance ratio, near-axial inflow) and cruise (propeller-mode, higher inflow velocity). Rotating-frame (MRF) analysis planned as a follow-up phase to extract thrust and power at design RPM. Project detail: Rotor: 3× fixed-tilt proprotors, diameter ≈ 0.91 m, mid-span chord ≈ 72 mm (2-blade, solidity ≈ 0.10), root t/c ≈ 18–20% tapering to tip t/c ≈ 10–12%. Baseline section NACA 64-210; validation against published 6-series wind-tunnel polars at matched Re. Cruise target range 14–22 m/s, hover thrust required ≈ 13 N per rotor at MTOW ≈ 4 kg (design-point estimate, pending structural mass buildup). Goal: characterize Cl/Cd/stall behavior across the hover-to-cruise transition envelope to inform final blade taper and section selection.
0
0
martianman1729 created this project
9 days ago
1 Geometry 1 Mesh 1 Simulation setup 1 ResultWhat is the project goal: Aerodynamic performance evaluation of the primary rotor blade (NACA 64-210 baseline, root-to-tip taper) for a solar-powered tilt-rotor eVTOL, across hover and cruise operating conditions. This blade forms part of the Sthiratej platform, a Low-Altitude eVTOL under development for coastal dark-vessel and IUU fishing surveillance. Simulation type: Steady-state RANS (SST k-ω, transition-enabled) for 2D/3D airfoil polar sweep across angle of attack, at two Reynolds number regimes corresponding to hover (low advance ratio, near-axial inflow) and cruise (propeller-mode, higher inflow velocity). Rotating-frame (MRF) analysis planned as a follow-up phase to extract thrust and power at design RPM. Project detail: Rotor: 3× fixed-tilt proprotors, diameter ≈ 0.91 m, mid-span chord ≈ 72 mm (2-blade, solidity ≈ 0.10), root t/c ≈ 18–20% tapering to tip t/c ≈ 10–12%. Baseline section NACA 64-210; validation against published 6-series wind-tunnel polars at matched Re. Cruise target range 14–22 m/s, hover thrust required ≈ 13 N per rotor at MTOW ≈ 4 kg (design-point estimate, pending structural mass buildup). Goal: characterize Cl/Cd/stall behavior across the hover-to-cruise transition envelope to inform final blade taper and section selection.
