In aerodynamic testing, the drag coefficient CDC_DCD of a specialized wing profile is modeled using the following definite integral related to the airflow pressure distribution:
CD=∫2312(4−w2)32 dw C_D = \int_{\sqrt{2}}^{\sqrt{3}} \frac{12}{(4 - w^2)^{\frac{3}{2}}} \, dw CD=∫23(4−w2)2312dwBy using the substitution w=2sinθw = 2 \sin \thetaw=2sinθ, determine the exact value of CDC_DCD.
