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temperature is standard 223k
(b) Consider an airplane flying at an altitude of 10,000m. Assume atmospheric...
Consider an airplane flying with a velocity of 40 m/s in conditions identical to those at...
Consider an airplane flying with a velocity of 40 m/s in conditions identical to those at an altitude of 5 km in the standard atmosphere. At a point on the wing, the airflow velocity is 70 m/s. Calculate the pressure at this point. Assume inviscid, incompressible flow and the U.S. Standard Atmosphere is the relevant atmospheric model.
An airplane is flying at 15,000 feet at mach 0.6. What is the true airspeed? What...
An airplane is flying at 15,000 feet at mach 0.6. What is the true airspeed? What temperature and total pressure would be measured on the pitot probe? If the airplane decreased its speed by 10 percent, what would be the new temperature, pressure, and density?
When an airplane is flying 200 mph at 5000-ft altitude in a standard atmosphere, the air...
When an airplane is flying 200 mph at 5000-ft altitude in a standard atmosphere, the air velocity at a certain point on the wing is 273 mph relative to the airplane. Please provide the gage pressure (units of lb per square feet) at the location on the wing where the wind speed (from the perspective of the wind) is 273 mph. Provide your answer with two significant figures.
Concorde The Concorde supersonic transport flew at M = 2.2 at 20 km altitude. Air is...
Concorde The Concorde supersonic transport flew at M = 2.2 at 20 km altitude. Air is decelerated isentropically by the engine inlet system to a local Mach number of 1.3. The air passed through a normal shock and was decelerated further to M = 0.4 at the engine compressor section. Assume, as a first approximation, that this subsonic diffusion process was isentropic and use standard atmosphere data for freestream conditions. -Determine the temperature, pressure and stagnation pressure of the air...
Velocity data analysis: Air flow speed is tested using a Pitot tube. Table 1 summarizes the...
Velocity data analysis: Air flow speed is tested using a Pitot tube. Table 1 summarizes the Power supply of the wind tunnel and the dynamic pressure DP. The dynamic pressure P, is the difference between the total pressure P, and the static pressure P, measured by the Pitot tube. Please determine: 1) the air flow speed at each power supply (consider room 2) Plot the flow speed vs power supply using a computer 3) If the relation of the flow...
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it...
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it is flying through to be calorically perfect Air. The air-data system measures the following quantities: freestream static pressure is 6.5 kPa, Pitot pressure is 36.75 kPa, total temperature is 433 K. (a) freestream Mach number, M.. (b) freestream static temperature, T. (c) freestream velocity (air speed), U. 4. Supersonic gas enters a duct with a constant area at M - 2.5 at a pressure...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor ro...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor rotates at a speed of 15000 rpm. The overall stagnation pressure ratio due to compression is 10.1, it was recorded that the air flows at a rate of 16 kg/s. The stagnation properties at the inlet are 215 kPa and 460K. The poly-tropic efficiency of the compressor is 90%. Assume the mean radius of the compressor is constant and equal...
. A turbofan aircraft engine is flying at 720 km/h at an altitude of 6100 m,...
. A turbofan aircraft engine is flying at 720 km/h at an altitude of 6100 m, where the ambient conditions are 50 kPa and -12°C (a negative value). The pressure ratio across the compressor is 13, and the turbine inlet temperature (TIT) is 1330 K. Assuming ideal operation for all components and constant specific heats for the air at room temperature (cold air model). (a) Sketch the T-s diagram of the cycle, and determine: (b) The Mach number of the...
Problem 8 Because pressure falls with increasing altitude, water also boils at a lower temperature. Consequently,...
Problem 8 Because pressure falls with increasing altitude, water also boils at a lower temperature. Consequently, food generally require more time to cook at higher elevations. Determine the boiling temperature of water at sea-level, 1000 m, and 2000 m above sea-level. Assume standard atmospheric conditions.
Consider a low speed, steady flow around the thn airfoil shown in figure below We know the velocity and altitude at which the vehicle is flying Thus, we know P. (ie, P) and U(ie. U) We have obtai...
Consider a low speed, steady flow around the thn airfoil shown in figure below We know the velocity and altitude at which the vehicle is flying Thus, we know P. (ie, P) and U(ie. U) We have obtained experimental values of the local velocity U, U,U at Pots 2, 3 and 4 Pontat the stagnation point of airfoil Point 3 at a point in the inviscid region just Edge of boundary layer Point outside the thin boundary layer Point 4...
Concorde The Concorde supersonic transport flew at M = 2.2 at 20 km altitude. Air is decelerated isentropically by the engine inlet system to a local Mach number of 1.3. The air passed through a normal shock and was decelerated further to M = 0.4 at the engine compressor section. Assume, as a first approximation, that this subsonic diffusion process was isentropic and use standard atmosphere data for freestream conditions. -Determine the temperature, pressure and stagnation pressure of the air...
Velocity data analysis: Air flow speed is tested using a Pitot tube. Table 1 summarizes the Power supply of the wind tunnel and the dynamic pressure DP. The dynamic pressure P, is the difference between the total pressure P, and the static pressure P, measured by the Pitot tube. Please determine: 1) the air flow speed at each power supply (consider room 2) Plot the flow speed vs power supply using a computer 3) If the relation of the flow...
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it is flying through to be calorically perfect Air. The air-data system measures the following quantities: freestream static pressure is 6.5 kPa, Pitot pressure is 36.75 kPa, total temperature is 433 K. (a) freestream Mach number, M.. (b) freestream static temperature, T. (c) freestream velocity (air speed), U. 4. Supersonic gas enters a duct with a constant area at M - 2.5 at a pressure...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor rotates at a speed of 15000 rpm. The overall stagnation pressure ratio due to compression is 10.1, it was recorded that the air flows at a rate of 16 kg/s. The stagnation properties at the inlet are 215 kPa and 460K. The poly-tropic efficiency of the compressor is 90%. Assume the mean radius of the compressor is constant and equal...
Consider a low speed, steady flow around the thn airfoil shown in figure below We know the velocity and altitude at which the vehicle is flying Thus, we know P. (ie, P) and U(ie. U) We have obtained experimental values of the local velocity U, U,U at Pots 2, 3 and 4 Pontat the stagnation point of airfoil Point 3 at a point in the inviscid region just Edge of boundary layer Point outside the thin boundary layer Point 4...
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