Low thrust propulsion systems are required for microspacecraft operations. For thruster systems that utilize gas expansion through micronozzle geometries, the operation at low Reynolds number is required. Cold gas flows are compared for a thin-walled, underexpanded orifice and a conical nozzle as a function of Reynolds number. The orifice diameter and the conical nozzle throat diameter are both 1.0 mm. The Reynolds numbers investigated range from below 1 to nearly 400. The nozzle to orifice thrust ratio is found to be below unity for Reynolds numbers below 70 for helium, argon and nitrogen propellants. For a thrust ratio below unity, the orifice is shown to have a higher propulsive efficiency when compared to the conical nozzle. The thrust measured in this study ranges from several hundred nano-Newtons to almost 1 mN. The thrust data is shown to transition from a free molecule solution at the low thrust range to nearly the continuum, inviscid solution at the high thrust range. Thrust data is presented for the same nozzle geometry over almost four orders of magnitude in thrust.