Consider a rectangular wing with a NACA 0009 airfoil section spanning the test section of a wind tunnel. The test section airflow conditions are sea level standard with a velocity of 176 ft/s. The wing is at an angle-of-attack of 4 degrees, and the wind tunnel force balance measures a lift of 29.5 lbf. You are solving for the area of the wing. Write the equation in terms of variables first and then solved for the area with values. (You do not need to define in words what each of the variables are. If needed, assume the smallest Re that you have data for.)