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

Info iconThis preview shows pages 1–10. Sign up to view the full content.

View Full Document Right Arrow Icon
AE 1350 Lecture Notes #7
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
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
Background image of page 2
Topics To be Studied Airfoil Nomenclature Lift and Drag forces Lift, Drag and Pressure Coefficients
Background image of page 3

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
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
Background image of page 4
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.
Background image of page 5

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Airfoil Chord Line Camber Line Equal amounts of thickness is added to camber in a direction normal to the camber line.
Background image of page 6
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.
Background image of page 7

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
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 .
Background image of page 8
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
Background image of page 9

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Image of page 10
This is the end of the preview. Sign up to access the rest of the document.

Page1 / 30

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

This preview shows document pages 1 - 10. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online