Rotational Derivatives of the Wing-in-Ground Aerodynamic Coefficients near Media Interface Surface and Their Specifics

Aeronautical and Space-Rocket Engineering


Аuthors

Vshivkov Y. F.1*, Gramuzov E. M.2**, Krivel' S. M.1, 3***, Khoilov V. V.1****

1. Irkutsk state university, Irkutsk, Russia
2. Nizhny Novgorod State Technical University n.a. R.E. Alekseev, 24, Minin Street, Nizhny Novgorod, 603950, Russia
3. Irkutsk National Research Technical University, 83, Lermontov str., Irkutsk, 664074, Russia

*e-mail: 1988ufv@mail.ru
**e-mail: terkor54@mail.ru
***e-mail: krivel66@mail.ru
****e-mail: khoilov2000@gmail.com

Abstract

The article presents a technique for determining and the results of the partial derivatives studies of aerodynamic coefficients of a wing and an aircraft near a solid interface according to the motion parameters characterizing the aircraft rotation around the center of mass and a change in its angle of attack. These are partial derivatives of the coefficients of aerodynamic forces and moments by the rotational motion parameters of the object, namely, the dimensionless angular velocities of the aircraft rotation relative to the axes of the associated coordinate system in roll, yaw, pitch and, separately, the dimensionless rate of the angle of attack changing. The results of the studied object flow-around modeling with CFD-systems based on tunable computational grids are employed as initial data for the derivatives determining. In fact, a moving model of the studied object is being considered in the computational domain (in a virtual wind tunnel). The laws of the object motion with such changes in the kinematic parameters of motion are being defined, which allow determining partial derivatives of the aerodynamic coefficients according to certain kinematic parameters in the vicinity of a fixed initial parametric point. An assessment of the computational results reliability compared to the known solutions has been performed. In comparison with the known exact and theoretical solutions based on the discrete vortex method, the reliability is tolerable. The authors demonstrated strong dependence of the partial derivatives of aerodynamic coefficients on the relative distance of the object from the interface, in some cases on the direction of rotation of the object in pitch, roll, yaw, and the direction of change in the angle of attack. The article presents the results of the computational experiment on the rotational derivatives determining of a tandem scheme wing-in-ground. Dependences of the wing-in-ground aerodynamic characteristics in flight near the screen surface depend non-linearly on the kinematic parameters of motion, in particular, and on the flight altitude (distance) above the screen. For this reason, the rotational derivatives of the aerodynamic coefficients of the wing-in-ground largely depend on the position, including the sign. The wing-in-ground rotation direction or the angle of attack changing impact on values and signs of the rotational derivatives is rather important. Unquestionably, these facts should be accounted for when analyzing the aerodynamics and flight dynamics of an aircraft near a screen by partial derivatives of the aerodynamic coefficients.

Keywords:

non-stationary aerodynamic characteristics of the wing-in-ground, coefficients of damping forces and moments, aerodynamic characteristics of the ekranoplan, GEV (ground-effect vehicle), (wing-in-ground-effect)

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