A quick calculation to check feasibility: Static propeller thrust T = ³√(P² ✕ η² ✕ Η² ✕ π ✕ (d²/2) ✕ ρ) Where: T is thrust in Newtons P is power of motor in Watts η is propeller efficiency, 1 is perfect Η is motor efficiency, 1 is perfect d is propeller diameter in meters ρ is air density in kg/m³ Known numbers: P = 350 W, or 175 W per rotor (a simplification, but close enough) d = 1.2 m ρ = 0.013 kg/m³ at Mars' surface Using typical efficiencies for propellers and motors: η = 0.75 Η = 0.9 Mass of helicopter in Mars' gravity is 0.68 kg. Using these numbers for one rotor: T = ³√(30625 ✕ 0.56 ✕ 0.81 ✕ 3.14 ✕ 0.72 ✕ 0.013) ≈ 7.4 N 7.4 N is around 0.75 kg of thrust for a single rotor - more than the helicopter's weight on Mars. So with both rotors it'll have more than enough thrust to fly there.