The measured lift slope for the NACA 23012 airfoil is 0.1080 degree−1 , and αL=0 = −1.3 ◦ . Consider a finite wing using this airfoil with AR = 8 and taper ratio of 0.8 which corresponds to τ = 0.054 and e = 0.95. Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack of 3◦ . CL ≈ 0.37 and CDi ≈ 0.006.

Air inially occupying a volume of 1 m2 at 100 kpa, 27 c undergoes three internally reversible processes in series. process 1-2 compression to 500 kpa during which pv constant process 2-3 adiabatic expanslon to 100 kpa process 3-1: constant-pressure expansion to 100 kpa (a) calculate the change of entropy for each of the three processes. (b) calculate the heat and work involved in each process. (c) is this cycle a power cycle or refrigeration cycle?