The object of the present study is a thruster with anode layer (TAL). Interest in such thrusters has recently increased due to their relative simplicity and manufacturability, which is especially important in large-scale production. In this work a study of the thrust characteristics and operational features of the TAL on krypton, a krypton-xenon mixture and xenon were carried out. During the tests the effect of the acceleration channel depth and the propellant flow rate on the discharge current, thrust, specific impulse, thrust efficiency, power-to-thrust ratio, and ion current to the body of TAL was determined. During the experiments the discharge voltage was 300 V, and the propellant flow rate varied from 1.5 to 3.5 mg/s. It was found that the dependence of the power-to-thrust ratio of the thruster on the acceleration channel depth has an extreme character with a pronounced maximum, while the thrust efficiency tends to saturate with an increase in the acceleration channel depth. The character of the thruster operation with the krypton-xenon mixture (the magnitude of magnetic fields, temperature mode, and boundaries of stable operation) is close to the TAL operation with pure krypton.