[nikhiljohn]

I have an airfoil (2d) of chord length 1 meter. The length of the camber line is 1.06m. The cross sectional area (2d enclosed area) is 0.17 meters. What should I give as the reference area if fluent for getting the correct cl.

Thanks everyone in advance for your help.

[AdrienL]

Most of the time Airfoils use the square of the chord length as the reference area

Sincerly

Adrien

[nikhiljohn]

Thanks You

[smab]

I have my NACA 23015 airfoil(flow speed 36m/s) which has a chord length of 100mm, max thickness 15.05mm,...
after scaling the grid to metres...what should be the reference values for area, length and depth...
i am unable to obtain correct values for Cl and Cd...please help
its very urgent....

[nikhiljohn]

The reference area should be your chord length (after scaling) and leave the length and the depth with the default values.

[Far]

Just want to add something.

Reference area is Length and depth. Since depth is taken as 1, therefore reference area for 2d airfoil is taken as c * 1 = Chord length

[pappusam]

Originally Posted by AdrienL

Most of the time Airfoils use the square of the chord length as the reference area

Sincerly

Adrien

kindly could you tell me, from where you have taken this? (i.e. ref. area = square of the chord length)

[NonStopEagle]

Originally Posted by pappusam

kindly could you tell me, from where you have taken this? (i.e. ref. area = square of the chord length)

Alright so, for an airfoil (i.e a 2-d section of a wing), the formula for cl is,
cl = lift/(0.5)*rho*(v^2)*c
where c is the chord length. Since there is no depth in a 2-d simulation, the depth value in the reference values is set to 1. reference area in fluent then has to be the length that you input (i.e. the chord length).
the reference area then becomes,
reference area = length*depth = chord*1 = chord.
So if you are running a 2d simulation of an airfoil, no matter the camber, always take the reference area as the chord.

[Narendhiran_IIT_Madras]

Hi everyone,
I need some clarity on the reference area calculation of 2D airfoil in fluent
For example: Chord =0.1 m, then reference area = chord * depth.
By default(2D airfoil) depth =1. i.e.1 m
so, ref area = 0.1*1=0.1 m^2, Physically it represents an airfoil with chord 0.1 m and depth(span)=1 m...

So my question is "Does the default depth value(=1) for 2D airfoil gives correct reference area?"

[orborneee]

Originally Posted by Narendhiran_IIT_Madras

Hi everyone,
I need some clarity on the reference area calculation of 2D airfoil in fluent Super Mario
For example: Chord =0.1 m, then reference area = chord * depth.
By default(2D airfoil) depth =1. i.e.1 m
so, ref area = 0.1*1=0.1 m^2, Physically it represents an airfoil with chord 0.1 m and depth(span)=1 m...

So my question is "Does the default depth value(=1) for 2D airfoil gives correct reference area?"

The exercise is really difficult, I'm still working on it step by step