Abstract
Testing the impact of the drag coefficient on an F16 aircraft model, depending on the angle of attack a was performed. First, a navigation model was introduced describing the preliminary and computational assumptions of the model. The final part of the present paper contains the relationships between the wind angle and the wind correction angle at the angle of attack a = 00, a = 110, a = 130 for a full-scale F-16 aircraft. The tables present results of all the calculations for individual angles of attack, taking into account variable wind angles relative to the longitudinal axis of the runway. The values show the corrections calculated for an 1/19 scale aircraft model and for a full-scale F16 aircraft. The "right" and "left" designations represent the direction from which the wind blows in relation to the aircraft.
Highlights
Accurate determination of the aircraft’s position has always been one of the fundamental reasons for existence of the air navigation
In order to develop a method for the position prediction, experimental studies of aerodynamic characteristics were used, which were performed in the wind tunnel with a measurement space diameter Q = 1.1 m, which belongs to the Military University of Technology, Warsaw Poland
3.1 Analysis of the drag coefficient influence on the F-16 aircraft model depending on the angle of attack a [4]
Summary
Accurate determination of the aircraft’s position has always been one of the fundamental reasons for existence of the air navigation. This allows pilots to perform air operations safely and accurately. Prediction of the aircraft’s position during the landing approach may be used in order to reduce the pressure placed on pilots at that time. Tests were performed for asymmetric flow at sideslip angles of up to β = - 300 to 300 at every 20 for angle of attack, α = 00, α = 110, α = 130,which, according to the Flight Manual, correspond to the angles occurring during the landing approach.
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