Green aviation is one of the most prosperous areas of civil aviation. Subjected to both battery energy density and motor power density, electric propulsion will be used in general aircraft at first stage of electric civil aviation. As to battery and motor technology progresses in the near future, conceptual design of distributed commuter airplane is performed aim to remote region transport in this paper. Firstly, the range and payload of electric airplane are studied according to battery energy density and lift-drag ration. Results show that, with battery power density 400~500wh/kg, the range will be 300~500km. if battery power density is 800wh/kg, the range will be 600~1000km. However, without breakthrough in battery area, main range of electric airplane is limited to 500~1000km and extreme range is less than 1500km. Secondly, integration design of airplane and propulsion is studied with respect to electric distributed propulsion configuration. The distributed propulsion system consists of many high-lift propellers which pulls aircraft and enhances downstream wing lift. Results show that, induced velocity distribution along blade radial direction has significant effect on wing lift increment. Besides, motor power and flight velocity are critical to the proportion of lift increment to wing lift without high-lift propeller slipstream. Increasing motor power, the proportion increases too. While, increasing flight velocity, the proportion decreases. Both high-lift propeller motor power and flight velocity should be decided by the aircraft overall design. At last, a conceptual scheme of commuter airplane aimed to remote region transport is depicted with total take-off weight 1400kg, range 500km, payload 250kg. Battery energy density 400wh/kg is used and lift-drag ration of airplane is 16 in the conceptual scheme. Distributed propulsion system consists of 10 high-lift propellers with 10kw motor power and a 120kw main propeller. And the high-lift propellers are operated during take-off and landing phases.