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Angle Of Attack Formula:
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Angle of Attack (α) is the angle between a reference line on a body (such as an aircraft wing) and the vector representing the relative motion between the body and the fluid through which it is moving. It is a fundamental parameter in aerodynamics that affects lift and drag forces.
The calculator uses the angle of attack formula:
Where:
Explanation: The formula calculates the angle of attack using the inverse tangent function applied to the ratio of yaw axis velocity to roll axis velocity.
Details: Accurate angle of attack calculation is crucial for aircraft performance analysis, stall prediction, flight control systems, and aerodynamic design optimization.
Tips: Enter velocity along yaw axis and velocity along roll axis in m/s. Both values must be positive numbers, with roll axis velocity greater than zero.
Q1: What is the typical range for angle of attack?
A: For most aircraft, angle of attack typically ranges from -5° to 15° during normal flight operations, with stall occurring at higher angles.
Q2: How does angle of attack affect aircraft performance?
A: Angle of attack directly influences lift and drag forces. Increasing angle of attack increases lift up to a critical point (stall angle), beyond which lift decreases dramatically.
Q3: What's the difference between angle of attack and pitch angle?
A: Angle of attack is the angle between the chord line and the relative wind, while pitch angle is the angle between the aircraft's longitudinal axis and the horizon.
Q4: Why is angle of attack important for stall prevention?
A: Aircraft stall when they exceed the critical angle of attack. Monitoring and controlling angle of attack is essential for stall prevention and flight safety.
Q5: Can this formula be used for all flight conditions?
A: This basic formula provides the geometric angle of attack. For complex flight conditions, additional factors such as airflow separation and compressibility effects may need to be considered.