An airplane flies at a speed of 900 km/h, at an altitude of 10,000 m, where ρ = 0.413 kg/m3, μ = 1.46 × 10-5 N s/m2, T = 223 K, γ = 1.4. If the wing average chord is 4 m and transition from laminar to turbulent flow is expected at Re = 106, calculate the percentage of chord with laminar flow.