As a means of preventing ice formation on the wings of a small, private aircraft, it is proposed that electric resistance heating elements be installed within the wings. To determine representative power requirements, consider nominal flight conditions for which the plane moves at 100 m/s in air that is at a temperature of
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- 1. Consider an airplane similar to the Beechcraft Bonanza V-tail, single engine, light-weight private airplane. The characteristics of the airplane (shown above on the left) are: Aspect ratio = 6.2 Wing area = 181 ft² Oswald efficiency factor = 0.91 Maximum gross weight = 3,400 lb Zero-lift drag coefficient = 0.027 N1/330 ● 100 OPA The specific fuel consumption is 0.42 lb of fuel per HP per hour. Fuel capacity is 44 gallons. The airplane is powered by a single piston engine of 345 HP maximum at sea level. Assume that the power of the engine is proportional to the freestream density. The two-blade propeller has an efficiency of 0.83. Calculate the following: Power required at sea level. Maximum velocity at sea level. Power required at 12,000 ft. of altitude. Maximum velocity at 12,2000 ft. of altitude. Range at sea level. Endurance at sea level. Estimate how much "extra" range and endurance can be achieved by adding the wig-tip fuel tanks shown above on the right.arrow_forwardAn aircraft has a total mass of (1.26x10^2) kg and a wing area of (1.800x10^1) m2. It operated with an aerofoil section having C = 1.0 and CD=0.1. Assuming that the total drag of the wing represents the whole drag of the aircraft, find the power input required for to overcome gravity and take off. Assume density of air to be 1.2 kg/m3. Answer should be in Watts with three significant figures. Note: Your answer is assumed to be reduced to the highest power possible. Your Answer: x10 Answerarrow_forwardQuestion 3 of 7 > -/2 E View Policies Current Attempt in Progress The initially stationary 17-kg block is subjected to the time-varying force whose magnitude P is shown in the plot. The 37° angle remains constant. Determine the block speed at (a) t = 1.7 s and (b) t = 5.7 s. 144 17 kg 37 SH = 0.57 H = 0.44 6.5 t. s Answers: (a) At t = 1.7 s, v= i m/s (b) At t = 5.7 s, v= i m/sarrow_forward
- Qs. An aircraft is flying in level flight at a speed of 200 km/h through air (density, p = 1.2 kg/m³, and viscosity, μ = 1.6 x 10-5 N-s/m²). The lift coefficient at this speed is 0.4 and the drag coefficient is 0.0065. The mass of the aircraft is 800 kg. The effective lift area of the aircraftarrow_forwardRequired information A disk-gap-band parachute has a drag of 1600 lbf when tested at 15 mi/h in air at 20°C and 1 atm. The diameter of the parachute is 43 ft. For air at 20°C and 1 atm, take p≈ 1.20 kg/m³. Take π = (22/7). If the drag on Mars is 65,000 lbf and the velocity is 1300 mi/h in the thin Mars atmosphere and p≈ 0.020 kg/m³, what is the drag coefficient on Mars? The drag coefficient isarrow_forwardThe friction coefficient for a boundary layer is given by the expression: Cf = 1.32 √ReT If the average flow velocity increases from an original state to a new state by a factor of 3.38, calculate the ratio of the Cf over its value at the original state.arrow_forward
- A jet airplane weighs 160,000 N and has a zero-lift drag coefficient of 0.008 and a wing area of 42 m2. At 100 m/s at sea level, the rate of climb is 11.5 m/s. The thrust developed by the engines is equal to 27,000 N. Determine the maximum rate of climb and the corresponding flight speed at sea level . [Answer: 21.6013 m/s and 214.5577 m/s]arrow_forwardAn aircraft has a total mass of (1.26x10^2) kg and a wing area of (3.000x10^1) m2. It operated with an aerofoil section having CL = 1.0 and CD=0.1. Assuming that the total drag of the wing represents the whole drag of the aircraft, find the power input required for to overcome gravity and take off. Assume density of air to be 1.2 kg/m3. Answer should be in Watts with three significant figures.arrow_forwardConsider a Boeing 747 airliner cruising at a velocity of 550 mi/h at a standard altitude of 38,000 ft, where the freestream pressure and temperature are 432.6 lb/ft2 and 390 R, respectively. A one-fiftieth scale model of the 747 is tested in a wind tunnel where the temperature is 430 R. Calculate the required velocity and pressure of the test airstream in the wind tunnel such that the lift and drag coefficients measured for the wind-tunnel model are the same as for free flight. Assume that both u and a are proportional to T 1/2. Let subscripts 1 and 2 denote the free-flight and wind-tunnel conditions, respectively. For C C2 and Co1 = Co2, the wind-tunnel flow must be dynamically similar to free flight. So, M, = M2 and Re, = Re,. %3D %3Darrow_forward
- An aircraft has a total mass of (1.18x10^2) kg and a wing area of (1.4000x10^1) m². It operated with an aerofoil section having C = 1.0 and Cp30.1. Assuming that the total drag of the wing represents the whole drag of the aircraft, find the power input required for to overcome gravity and take off. Assume density of air to be 1.2 kg/m3. Answer should be in Watts with three significant figures. Note: Your answer is assumed to be reduced to the highest power possible. Your Answer: x10 Answer DELL F4 F7 F8 F9 F10 F11 F12 PrtScr Insert Delete F5 F6 & Backsarrow_forwardThe friction coefficient for a boundary layer is given by the expression: Cf= If the average flow velocity increases from an original state to a new state by a factor of 4.66, calculate the ratio of the Cf over its value at the original state. 1.32 √Rexarrow_forwardA chair lift is to be installed from the surface down to a depth of 150 m. The inclination is 17 degrees to the horizontal. An operating velocity is to be used, and the system will be required to transport 300 persons per hour. Assuming the worst-case scenario, namely that no persons travel down while the system has a full load traveling up, determine: 1. the spacing of thr chairs 2. the traveling time per person 3. the output power of the motor required to drive the system Perfomance criteria: A force criteria: A force of 2 kN per 100 m of the length of the loaded part of the system is required to overcome friction. Mass per person: 70 kg Overall mechanical efficiency: 85%arrow_forward
- Principles of Heat Transfer (Activate Learning wi...Mechanical EngineeringISBN:9781305387102Author:Kreith, Frank; Manglik, Raj M.Publisher:Cengage Learning