Hi, you need to create an airfoil curve around the airfoil at any particular section (usually by intersection plane method) and plot the static pressure around the airfoil. By this method you can plot Cp along the chord for both suction and pressure surface at a particular section.
@@dangbk99 We take difference between inlet freestream total pressure and static pressure to calculate the dynamic pressure directly. Velocity is not calculated.
How did you calculate the refrence area?
Hi, how do you calculate the Reference Area and Length for the for the reference values step?
How to show Cp or mach number, I haven't them in cf post
Hi, you need to create an airfoil curve around the airfoil at any particular section (usually by intersection plane method) and plot the static pressure around the airfoil. By this method you can plot Cp along the chord for both suction and pressure surface at a particular section.
@@LearnCAE What is your velocity in the formula for calculating Cp?
@@dangbk99 We take difference between inlet freestream total pressure and static pressure to calculate the dynamic pressure directly. Velocity is not calculated.
@@LearnCAE Can you give me a reference to the Cp variable's formula in the CDF post? I still don't understand
@@dangbk99 Kindly check this link en.wikipedia.org/wiki/Pressure_coefficient