Project 2D
̇ ̇ ̇ this means for incompressible
For incompressible flow:
Manometer: u-form tube with liquid, difference in height indicates the pressure difference
Speed of sound √
With manometer:
Pilot tube measures total pressure
The highest mach number on airfoil is where is the largest (close to the thickest point of
the airfoil)
Due to high angle of attack flow separation suddenly pressure difference
Project LI
Pressure coefficient:
Normal force coefficient (Cn) : surface Cp upper wing side graph – surface of cp lower wing side graph
For you may assume
For tapping points on wing :
Negative Cp is plotted upward so that the upper survase corresponds with the upper curve of graph
Decreasing speed gives a higher Cp and shifts the whole Cp curve up
For speeds above M=0,3 the pressure coefficient changes to different formula
At thickest part of airfoil the curves of Cp are at lowest point
Maximum Cp is 1 near leading edge in stagnation point
For symmetrical airfoil
̇ ̇ ̇ this means for incompressible
For incompressible flow:
Manometer: u-form tube with liquid, difference in height indicates the pressure difference
Speed of sound √
With manometer:
Pilot tube measures total pressure
The highest mach number on airfoil is where is the largest (close to the thickest point of
the airfoil)
Due to high angle of attack flow separation suddenly pressure difference
Project LI
Pressure coefficient:
Normal force coefficient (Cn) : surface Cp upper wing side graph – surface of cp lower wing side graph
For you may assume
For tapping points on wing :
Negative Cp is plotted upward so that the upper survase corresponds with the upper curve of graph
Decreasing speed gives a higher Cp and shifts the whole Cp curve up
For speeds above M=0,3 the pressure coefficient changes to different formula
At thickest part of airfoil the curves of Cp are at lowest point
Maximum Cp is 1 near leading edge in stagnation point
For symmetrical airfoil
