ATR 42 Lift coefficient data
 

Anyone aware of where I can get ATR 42 model lift coefficient data, Cl, Cd..
pls?

and AFM also :)

thanks

The only info I have to hand.

Wing Root RA 1843 (NACA 43018 mod)
Wing Tip RA 1343 (NACA 43013 mod)

hi, i want to calculate the lift force and drag force during a typical landing for ATR 42 aircraft and canadair regional jet..
there for i need the CL and Cd values to calculate those forces for a flap setting (e.g.40). would u have any reasonable values to use for this?

thanks

coefficient of drag/ lift
 

any one has any data, or reasonable estimate of a Coefficient of lift (Cl) and coefficient of draf (Cd) that i can use to calc stopping distance during landing, for aircraft of similar type to ATR 42, Canadair RJ or Fokker 50 ?

please

Well, why don't you take ATR's landing weight of, say 18000 kg, approach speed of about 110 KT (55m/s) and calculate back the lift coefficient Cl? As for drag, I can only "guesstimate" that lift/drag ratio in landing config might be approx 1:10, so Cd = 0,1*Cl...

Rough estimate, but better than nothing...

Other idea to estimate Cd in landing config: ATR in on approach in landing config is using approx 20% torque. at 82%Np. According to my "back of tha fag packet" calcs this equals to approx 440Hp per engine. Knowing the power requred you may calculate back the drag coefficient. In these calculations, you should take into account that the following figrues are valid for a 3 deg flight path, and that part of the weight vector is "helping" to overcome the drag... Also, you should make some allowance for propeller efficiency...

P.S. The above is for ATR-42-500, which has bigger engines and is heavier thane the original 42-300

thanks thanks:ok::ok: