Answer Happy

(a) The following information in Table Q2, is for a commercial airliner during a high- altitude steady level cruise. Reference Geometry Wing areas 479 m2 Wing span 76.61 m Flight conditions Altitude 12,192 m Density 0.30276 kg/m3 TAS 280.15 m/s Mass properties Weight 2,833,500 N Aerodynamic coefficients Oswald's efficiency factor e 0.8 Zero Lift Drag Cdo 0.023 Table Q2

Using the information in Table Q2 above, calculate; (i) The wing Aspect Ratio [2] (ii) The K value of the parabolic drag polar [2] (iii) The Equivalent airspeed (EAS) [2] (iv) The Cl at cruising altitude [4] (v) The Co at the same altitude [4] (vi) The lift to drag ratio and hence the Drag experienced at this altitude. [2] (b) (i) Which region of the Earth's atmosphere is the aircraft flying in and why would the pilot choose to fly in this region? [2] (ii) If the thermometer on the aircraft read a temperature value of -46.5°, the aircraft would be flying at ISA +/- _? [2]