Here are some elements for validation of MIAReX calculation algorithm.
With linear theory for airfoil bahoviour, you can find an analytical
solution to the elliptical planform problem, that we'll call "exact".
Here we will check that MIAReX algorithm fits with this exact solution.
After about 15 iteration, convergence criteria is reached. We get the
same value as exact analytical value with MIAReX.
There are some "side effects", due to discretization. Those effects are not seen on the gloables coefficients.
|We verify the classical result that, for elliptical wing, Cl is constant along span. The value reached is the same as exact analytical result.|
Exact value for Oswald on elliptical wing is Oswald=1.
We get exactly this result with MIAReX, as soon as the CL value is not too close to CL=0.
With those results, we can validate MIAReX concerning :
In NACA report youcan find many experimental result for finite wing, including airfoil and induced drag. Among those is : Naca TN-1270 : "Experimental and calculated characteristics of several NACA 44-series wings with aspect ratios of 8, 10, and 12 and taper ratios of 2.5 and 3.5".