MIAReX *,
"2,5D Wing Calculation"
A calculation method for Xfoil and multi-airfoil wings  * Méthode d'Intégration sur une Aile de Résultats eXpérimentaux & Xfoil
meaning Integral Method over a Wing for eXperimental and Xfoil Results MIAReX Validation

Here are some elements for validation of MIAReX calculation algorithm.

1. Linear theory : the elliptical wing

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.

• Induced angle following iterating

 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. • Cl distribution

 We verify the classical result that, for elliptical wing, Cl is constant along span. The value reached is the same as exact analytical result. • Oswald factor values

 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. Conclusion :
With those results, we can validate MIAReX concerning :
• Induced angle calculation algorithm
• Lift and induced drag coefficient calculation, as given by analytical linear 2D theory
.

2. Non linear theory on tapered wing (Naca TN-1270)

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".

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