The effectiveness of small aircraft of the aircraft type is largely determined by the characteristics of the bearing surfaces and the moment of rotation around the center of mass. Accordingly, the alignment and balancing of airplane-type aircraft in the longitudinal direction is considered as a responsible design task. Aerodynamic schemes differing in the level of bearing capacity losses for balancing moments became the object of research. In particular, balancing losses of the normal aerodynamic scheme, due to the use of a rearward horizontal feathering. Such losses are compensated for by an increase in wing area, which leads to an increase in structural mass, a decrease in payload and an increase in fuel consumption. For small-sized aircraft of the airplane type, such consequences mean deterioration of those parameters, in which they are already inferior to full-size aircraft due to their reduced size and flight speeds. Therefore, one of the ways to increase the carrying capacity of small-sized aircraft of airplane type is the use of such aerodynamic schemes, in which there is no loss of load-bearing properties of the structure for balancing. As an alternative two aerodynamic schemes are considered - “duck” and tandem. In them system of bearing surfaces consists of two flat surfaces, generating only positive lift force. In a duck, this is a wing and a horizontal fin located ahead of the wing. In a tandem, it is two wings located behind each other. And horizontal plumage. The rear wing performs the rear wing. Due to the fit to the fuselage, their bearing surfaces, if necessary, can be easily folded. According to the results of the conducted research, it was determined that the center line in the application of the “duck” and tandem schemes should be more rearward than in the normal aerodynamic scheme.