1. At what angle of attack (in deg.) must the airfoil be pitched to obtain zero lift? (answer expressed to the nearest hundredth) 2. At the burble point, what is the value of the lift coefficient? What is the stalling angle of attack (in deg.)? (all answers expressed to the nearest hundredth) 3. From the graphical solution, what is the maximum lift-to-drag ratio? What is the optimum angle of attack (in deg.)? (all answers expressed to the nearest hundredth) 4. Where the lift coefficient varies linearly with the angle of attack, approximate the lift curve slope (per degree, nearest hundredth) 5. For a chord length of 100 cm, determine the following? (all answers are in cm and rounded off to the nearest hundredth)