(You may neglect unsteady terms in your force balance.) 2. Calculate the minimum airplane speed during take off, with and without flaps extended. Climax indicates the largest value of the lift coefficient before stall. I - 3.5t Double-slotted 3.0 flap Double-slotted flap 2.67 Slotted flap Slotted flap 52 Clean (no flap) 0.5 Clean (no flap) 0.51 -5 20 0.05 0.10 0.15 0.20 0.25 0.30 0 5 10 15 Angle of attack, a(deg.) Figure 1: Lift and Drag coefficients for a NACA23012 airfoil with and without flaps. You may neglect wind speed in all calculations. At cruising altitude, the air density is p=0.3 kg/m'.
During take off, the air has a density Pro = 1.2 kg/m². The wing has double-slotted flaps that are used for increasing lift during take off and landing only (i.e.
Its wings are approximated by NACA23012 airfoils (see characteristics below), with constant width and a total wing planform area (both wings) of 125 m2. Transcribed image text: A Boeing 737 airplane has a mass of 80000 kg.
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