Engineering, 29.10.2019 06:31 Kategaldamez3
Consider the propeller-driven general aviation aircraft in steady level longitudinal flight with a constant lift coefficient of 0.95.
a) what is the range of the aircraft in flight at an altitude of 2,000 ft? what are the initial airspeed, elevator deflection, and throttle setting with a full fuel tank? what are the terminal airspeed, elevator deflection, and throttle setting when the fuel tank is empty?
for a propeller-driven general aviation aircraft, wing surface area is 175ft^2. weight of the aircraft with a full tank is 2,900lbs. weight of the aircraft with an empty tank is 2,530lbs. the power specific fuel consumption rate is 0.45lb fuel/hr/hp. the air density at an altitude of 2000ft is 2.2409x10^-3 slug/ft^3. k=0.054. cd=0.026.
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