A development variant of a high-performing engine using RP-1 and LOX demonstrated in ground tests at sea level the characteristic velocity c₁∗ =1765 m/s, thrust coefficient CF,₁ =1.76, and exit Mach number Mₑ =3.50. Assume that the ideal rocket approximation is valid; the molecular weight of the expanding propellant gas is =23.5 and its specific heat ratio is γ=1.148 Calculate a) specific impulse of the engine Iₛₚ,₁ at sea level.