### A Numerical Criterion for F-16 Fighter Pitch Maneuver Boundary

#### Abstract

Enter the motor of the initial state, speed, height of the maneuver process also has an important influence in the stall maneuver in. This is due to different flight height and velocity will produce different aircraft dynamic pressure, which leads to the torque changes, and then make the maneuver process is complete different. Specific for the F-16 aircraft, due to the aircraft aerodynamic coefficient and moment coefficient is only attack angle, sideslip angle, the control function of the rudder and the leading edge of the flap angle, flight height and velocity and will not affect the aerodynamic coefficient and moment coefficient - in other words, the under the conditions of different flight height and velocity, so long as has the same attack angle , sideslip angle , the control rudders and leading edge flap angle, the aircraft will be with the same aerodynamic coefficient and moment coefficient. Due to the different flight speed and altitude, the dynamic pressure is different, which makes the aerodynamic force and moment of the flight. By the above situation shows that, when the aircraft in different speed and height of the BRDF maneuver, the torque coefficient of the same, engine can provide the thrust and thrust vector of available control arm of force of a certain, torque is different, thus leading to, when the aircraft dynamic pressure reaches a threshold value, the operating torque reaches the limit value, unable to maneuver. For a certain class of aircraft, the thrust vector provided by the operating torque limit value, you can determine a flight boundary.

#### Keywords

Dynamic Pressure, Torque, Attack Angle

DOI

10.12783/dteees/edep2016/5956

10.12783/dteees/edep2016/5956

#### Full Text:

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