In this present approach using direct design method in Xflr open source software a newly designed low Reynolds number airfoil is validated. UIUC airfoil coordinates database is taken for the reference airfoil SS007 and, S1223 and E423. using Xfoil parameters, panel code the airfoil parameters like thickness, camber, camber location is optimized at different Reynolds number ranging from 3.42*105 to 10.28*105 at different angle of attacks . This notes derives largely from the prior publication (see refs [3]). The characteristics of new airfoil are analysed and validated from the reference airfoil SS007 which can produce a lift of 2.56 and high L/D ratio at stall angle. Application:This low Reynolds number airfoil is strongly recommended for mav design.