Scotracer wrote:timbo wrote:Scotracer wrote:I was just stating that if it's constant, it's an easy interpolation - none of the variables in F = rho*A*U^2*Cl change, apart from the velocity.
So, what's the units used to calculate Cl? Any guesses?
I used rho=1.21 kg/m^3, U=83.3m/sec, F=30kN and got A=2.75, probably square meters=)))
I guess it's too small for F1 car?
The coefficient of lift wont be calculated for an F1 car, it will be found in the wind-tunnel or CFD because it runs directly from chord length and plan area etc - something that isn't directly applicable.
Oh and I've been an eejit, it's F = 1/2*rho*A*U^2*Cl - woops
The area is the plan area - the surface area that the air is subject to. 2.75 (or whatever it is after you redo it without my idiocy included) on a car that is 4.5x1.8 metres does seem a bit low but when you consider the size of the floor and the wings, it might not be too far off.
2.6 sq m is the value for planform area? how come its that small cause ive model an f1 car (maybe not accurate but at least 80% is same as the regulation) and the planform area is around 5.4 sq m (auto calculation from CFD program)..
by using the value (timbo) " I used rho=1.21 kg/m^3, U=83.3m/sec, F=30kN "
Fd = Downforce
P = rho
V = velocity
A = planform area
Cl = lift coefficient
Fd = [ P*(V^2)*A*Cl ] / 2
30,000) = [ 1.21*(83.3^2)*5.4*Cl ] / 2
=> Cl = 1.323
why most reply stated that Cl is around 2.7?
by the way this is what i got from my cfd analysis and i dont know whether its correct or not..
1:5 scale model and its a half body
A = 0.109261 ( its /25/2 from full body)
P = 1.1458
V = 38.013 scaled from 85 m/s
Cl = 3.7
Fd = [ P*(V^2)*A*Cl ] / 2
= [ 1.1458*(38.013^2)*0.109261*3.7 ] / 2
= 343.709 (for scaled and half)
# im not sure if this is correct but if i want to find for the real size car, i need to multiply with 2 ( half body ) and multiply by 25 ( which is for scale )
so
Fd = 343.709*2*25
= 17,815.45 / 9.81
= 1705.73 kg
