The computational methods developed by TsAGI are widely applied for projecting airfoils.
These methods ensure integral and distributed aerodynamic characteristics of airfoils at subsonic and transonic speeds at regimes of separated and unseparated flows, including the regime of maximum lift force.
Complex physical investigations are carried out to determine features and processes of flow over wing airfoils.
Aerodynamics of Wings
TsAGI has developed new types of airfoils with peak and rear distributions of pressure (airfoils with rear load). These airfoils formed the basis for comprehensive computational and experimental investigations of aerodynamics of swept wings designed for cruising speeds M=0.8-0.85.
The starting point for all aerodynamic projects was optimization of a wing form and airfoil configuration for passenger airliners designed for various Mach numbers.
The following factors must be considered:
- suitable choice of the airfoil shape and thickness considering the angle of geometrical twist by the span
- providing the highest aerodynamic efficiency at design values of Mach number and Cy of the cruising flight
- maximum stability for passenger airliners under turbulent conditions and maneuvers with necessary «store» of Cy
- prevention of stalling and providing maximum longitudinal static stability at high critical and over- critical angles of attack through design of wing shape