Derive drag coefficient for f14 at max thrust and airspeed

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Reference no: EM13339809

he basic specifications for an F14 jet are as follows: Wingspan 64 m spread, 38 m swept Total Wing area Aw = 54.5 m2 Drag profile area Ap = 11.5 m2 Mass 27,700 kg fully loaded 2 x GE F110 Turbofan engines Thrust 61.4 kN from each engine, 124.7 kN each with afterburners lit Maximum airspeed Ma2.34 or 2485 km/h at 10 km altitude Peak Thrust/Weight ratio 0.91

a) Using the data, derive a drag coefficient for the F14 at maximum thrust and airspeed (ie with afterburners). Assume air temperature -56.5oC and pressure 26 kPa absolute at 10 km alt.

b) The lift coefficient at top airspeed is rated at 0.054. What lift does that generate? Is the fully loaded aircraft climbing or descending at 10 km altitude and top speed?

c) A 1:32 scale model F14 weighs 2.5 kg. What are the ratios of wing span, area and weight to the full scale? Assuming the drag and lift coefficients are in similar ratios to the peak performance coefficients in a) and b), what thrust does the model require at cruising speed?

d) Given c) and assuming a model drag coefficient 100x that of the prototype peak performance drag coefficient, what is the model's cruising speed near sea level at 15oC?

Reference no: EM13339809

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Derive drag coefficient for f14 at max thrust and airspeed : Wingspan 64 m spread, 38 m swept Total Wing area Aw = 54.5 m2 Drag profile area Ap = 11.5 m2 Mass 27,700 kg fully loaded 2 x GE F110 Turbofan engines Thrust 61.4 kN from each engine

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