Lecture.7

# Lecture.7 - AE 1350 Lecture Notes#7 We have looked at...

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AE 1350 Lecture Notes #7

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We have looked at. . Continuity Momentum Equation Bernoulli’s Equation Applications of Bernoulli’s Equation Pitot’s Tube Venturi Meter Pressures and Velocities over Airfoils
Topics To be Studied Airfoil Nomenclature Lift and Drag forces Lift, Drag and Pressure Coefficients

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Uses of Airfoils Wings Propellers and Turbofans Helicopter Rotors Compressors and Turbines Hydrofoils (wing-like devices which can lift up a boat above waterline) Wind Turbines
Evolution of Airfoils Early Designs - Designers mistakenly believed that these airfoils with sharp leading edges will have low drag. In practice, they stalled quickly, and generated considerable drag.

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Airfoil Chord Line Camber Line Equal amounts of thickness is added to camber in a direction normal to the camber line.
An Airfoil is Defined as a superposition of Chord Line Camber line drawn with respect to the chord line. Thickness Distribution which is added to the camber line, normal to the camber line. Symmetric airfoils have no camber.

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Angle of Attack α V Angle of attack is defined as the angle between the freestream and the chord line. It is given the symbol α . Because modern wings have a built-in twist distribution, the angle of attack will change from root to tip. The root will, in general, have a high angle of attack. The tip will, in general, have a low (or even a negative) α .
Section Sectional Drag, D´ Sectional Lift, L ´ The component of aerodynamic forces normal to the freestream, per unit length of span (e.g. per foot of wing span), is called the sectional lift force, and is given the symbol L ´. The component of aerodynamic forces along the freestream, per unit length of span (e.g. per foot of wing span), is called the sectional drag force, and is given the symbol D ´. V

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Lecture.7 - AE 1350 Lecture Notes#7 We have looked at...

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