bug

Author: juancamarotti

potential_flow/validation/naca0012_potential_incompressible_flow/README.md

@@ -56,5 +56,5 @@ The aerodynamic coefficients obtained from the simulation can be compared with r
 For an angle of attack of $\alpha = 5^\circ$, the computed lift coefficient is $C_l = 0.569$. This result shows very good agreement with the reference data presented in Figure 4, which is used here for validation purposes.
 
 ## References
-(1) [https://aerospaceweb.org/question/airfoils/q0259c.shtml] (https://aerospaceweb.org/question/airfoils/q0259c.shtml)
+(1) https://aerospaceweb.org/question/airfoils/q0259c.shtml