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(10 pts) An aircraft with a prop-driven 100 hp engine is flying at a speed of...
2. An aircraft with Coo -0.020, k0.12 is in steady, level flight at he -30,000 ft...
2. An aircraft with Coo -0.020, k0.12 is in steady, level flight at he -30,000 ft and Mo- me AR 08. The aircraft has a wing area of 375 ft, and it weighs 25,000 lb. Its CLmax İsl 8 a. b. c. d. e. Calculate the drag coefficient when Calculate the thrust the engine is producing. Calculate the horsepower the engine is producing Calculate the stall speed at that altitude Now the velocity is to be changed. Calculate the minimum...
For the C172D flying at sea level (density = 0.002377 slug/ft^3) with V∞= 95 knots (160ft/s), com...
For the C172D flying at sea level (density = 0.002377 slug/ft^3) with V∞= 95 knots (160ft/s), compute: Find : Lift coefficient Drag coefficient (L/D) ratio Thrust Required(TR) Power Required(PR) at IAS 50ft/s I found the CL, CD and L/D but I need help finding the TR and PR Wingspan 35.8 ft Wing area 174 ft22 Normal gross weight 2300 lb Fuel Capacity 38 Gal. of Aviation Gasoline Power Plant One 160 hp piston engine at sea level Specific fuel consumption...
be carefull with the unites , A Propeller driven aircraft is flying at sea level, the...
be carefull with the unites ,
A Propeller driven aircraft is flying at sea level, the given data are power available is Pa = 150000 watt, Weight=2500 Newton, K-0.05 and Cp, o=0.01 and S=12m2 density=1.225 kg/m3 calculate maximum velocity of the aircraft? Also find maximum load factor when V=40m/s in above?
Performance curves for a propeller/reciprocating engine driven aircraft W=3250 lbs H=6000ft Based on the graphs estimate...
Performance curves for a propeller/reciprocating engine driven
aircraft
W=3250 lbs H=6000ft
Based on the graphs estimate the maximum obtainable air time for
gliding from this altitude
Climb Hodograph 30 25 20 15 10 150 200 250 300 50 100 Horizontal Speed, ft/sec
A solid 1.25 in. diameter shaft is used in an aircraft engine to transmit 140 hp...
A solid 1.25 in. diameter shaft is used in an aircraft engine to transmit 140 hp at 2930 rpm to a propeller that develops a thrust of 1700 lb. Determine the magnitudes of the principal stresses and the maximum shear stress at any point on the outside surface of the shaft. Enter the principal stresses at any point on the outside surface of the shaft. Use the sign convention that a tension normal stress is positive and a compression normal...
For your selected aircraft, research and present the following information in your instructional presentation: Selected aircraft...
For your selected aircraft, research and present the following information in your instructional presentation: Selected aircraft – Boeing 787 (Dreamliner) Maximum takeoff weight (MTOW) – 557,000 lbs Engine type, number, and rated thrust, as well as total available thrust (sum of all engines) – 2 General Electric, GEnx-1B / Trent 1000, rated thrust; 64,000 lbf, total thrust; 128,000 lbs Takeoff distance at MTOW – 8,500 ft Utilizing the above-researched information, derive and present (in an instructional way) approaches and solutions...
Problem 7 (4 marks) Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane The...
Problem 7 (4 marks) Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane The airplane weight is 2950 lb and the wing reference area is 174ft2. The drag coefficient of the airplane Co is a function of the lift coefficient CL, such that C 0.025+0.054i a) For a steady level flight at sea level, where the ambient atmospheric density is 0.002377slug/ft3, plot on a graph the variation of Cu, CD, and the lift-to-drag ratio (L/D) with flight velocity...
What are the purposes of nozele design of an engine?(15 %) Prob. 4 A turbojet aireraft...
What are the purposes of nozele design of an engine?(15 %) Prob. 4 A turbojet aireraft is flying under the following conditions, please calculates the net thrust and the effective velocity. (20 %) Prob. 5 Aireraft fly speed-400 mph Inlet airflow-100 lb/s Exhaust nozzle area 3 ft Exhaust nozzle pressure 40 psia Exhaust gas velocity 1000 mph Fuel flow 3 lb/s steady speed of 900km/hr at an altitude where the temperature is 1700K. nies
What are the purposes of nozele...
sel engine for a commercial boat operates at 200 rpm and delivers 800 hp through a...
sel engine for a commercial boat operates at 200 rpm and delivers 800 hp through a 1) A die with a ratio of 4 to 1 to the propeller as shown below. Because the propeller shaft gearbox ed is four times that of the crank shaft, the torque on the propeller shaft is one-fourth that spe o the crank shaft. Both the shaft from the engine to the gearbox and the propeller shaft are to be solid and made of...
Please show full steps, will rate. A turbojet powered aircraft is flying at 250 m/s where...
Please show full steps, will rate.
A turbojet powered aircraft is flying at 250 m/s where the ambient temperature and pressure are -18 °C and 55 kPa, respectively. The pressure ratio for the compressor is 10, and the turbine inlet temperature is 1200 °C. The mass flow rate of air into the engine is 50 kg/s. a.) How much thrust does the engine develop? b.) How much heat must be added to the air in the combustor? c.) What is...
2. An aircraft with Coo -0.020, k0.12 is in steady, level flight at he -30,000 ft and Mo- me AR 08. The aircraft has a wing area of 375 ft, and it weighs 25,000 lb. Its CLmax İsl 8 a. b. c. d. e. Calculate the drag coefficient when Calculate the thrust the engine is producing. Calculate the horsepower the engine is producing Calculate the stall speed at that altitude Now the velocity is to be changed. Calculate the minimum...
be carefull with the unites ,
A Propeller driven aircraft is flying at sea level, the given data are power available is Pa = 150000 watt, Weight=2500 Newton, K-0.05 and Cp, o=0.01 and S=12m2 density=1.225 kg/m3 calculate maximum velocity of the aircraft? Also find maximum load factor when V=40m/s in above?
Performance curves for a propeller/reciprocating engine driven
aircraft
W=3250 lbs H=6000ft
Based on the graphs estimate the maximum obtainable air time for
gliding from this altitude
Climb Hodograph 30 25 20 15 10 150 200 250 300 50 100 Horizontal Speed, ft/sec
A solid 1.25 in. diameter shaft is used in an aircraft engine to transmit 140 hp at 2930 rpm to a propeller that develops a thrust of 1700 lb. Determine the magnitudes of the principal stresses and the maximum shear stress at any point on the outside surface of the shaft. Enter the principal stresses at any point on the outside surface of the shaft. Use the sign convention that a tension normal stress is positive and a compression normal...
Problem 7 (4 marks) Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane The airplane weight is 2950 lb and the wing reference area is 174ft2. The drag coefficient of the airplane Co is a function of the lift coefficient CL, such that C 0.025+0.054i a) For a steady level flight at sea level, where the ambient atmospheric density is 0.002377slug/ft3, plot on a graph the variation of Cu, CD, and the lift-to-drag ratio (L/D) with flight velocity...
What are the purposes of nozele design of an engine?(15 %) Prob. 4 A turbojet aireraft is flying under the following conditions, please calculates the net thrust and the effective velocity. (20 %) Prob. 5 Aireraft fly speed-400 mph Inlet airflow-100 lb/s Exhaust nozzle area 3 ft Exhaust nozzle pressure 40 psia Exhaust gas velocity 1000 mph Fuel flow 3 lb/s steady speed of 900km/hr at an altitude where the temperature is 1700K. nies
What are the purposes of nozele...
sel engine for a commercial boat operates at 200 rpm and delivers 800 hp through a 1) A die with a ratio of 4 to 1 to the propeller as shown below. Because the propeller shaft gearbox ed is four times that of the crank shaft, the torque on the propeller shaft is one-fourth that spe o the crank shaft. Both the shaft from the engine to the gearbox and the propeller shaft are to be solid and made of...
Please show full steps, will rate.
A turbojet powered aircraft is flying at 250 m/s where the ambient temperature and pressure are -18 °C and 55 kPa, respectively. The pressure ratio for the compressor is 10, and the turbine inlet temperature is 1200 °C. The mass flow rate of air into the engine is 50 kg/s. a.) How much thrust does the engine develop? b.) How much heat must be added to the air in the combustor? c.) What is...
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