An aircraft is flying at an altitude of 4500 m above sea level, where the ambient pressure, temperature and density are 57 kPa, 259 K and 0.777 kg/m³, respectively. The speed of the aircraft (V) is 230 m/s. Gas constant R=287 J/kg/K, and specific heat ratio γ=1.4. If the stagnation pressure is p_o, and static pressure is p, the value of (p_o-p)/(1/2 ρ V²) is ______ (rounded off to two decimal places).