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?
Homework Answers
At 15000ft, the pressure measures by the pitot probe will be 8.32psi and 5.55 fareheight True speed is 0.6*343= 205.8m/a
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An airplane is flying at 15,000 feet at mach 0.6. What is the
true airspeed? What...
temperature is standard 223k (b) Consider an airplane flying at an altitude of 10,000m. Assume atmospheric...
temperature is standard 223k
(b) Consider an airplane flying at an altitude of 10,000m. Assume atmospheric conditions from the standard atmosphere tables in the text. If the stagnation pressure measured by a pitot tube is po = 0.7929 atm, determine the Mach number of the vehicle. Also determine the air speed of the vehicle.
(a) A high speed (Mach number > 0.3) aircraft is flying at an altitude where the...
(a) A high speed (Mach number > 0.3) aircraft is flying at an altitude where the temperature and pressure is 2°C and 97 kPa. Its flight velocity is measured by a probe which records a dynamic pressure of 20 density is 13600 kg/ml. Find the reading of the manometer given k=1.4 and R=0.287 kJ/kg-K.
An airplane weighs 16,000 lbs and is flying at 5000 ft altitude and at an airspeed...
An airplane weighs 16,000 lbs and is flying at 5000 ft altitude and at an airspeed of 200 fps. Find (a) the potential energy, (b) the kinetic energy, and (c) the total energy. Assuming no extra drag on the airplane, if the pilot dove until the airspeed was 400 fps, what would the altitude be?
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa...
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa and measured (stagnation) temperature of 500 K. DISCUSSION: Suppose that, instead of assuming that a normal shock occurs upstream of the Pitot tube, it is assumed that the flow upstream is ISENTROPIC... what would the estimated flow speed be in that case? (NOTE: A normal shock is always observed to form upstream of bluff bodies such as...
2. (4) An airplane is trimmed straight and level at a true airspeed of 50 m/s...
2. (4) An airplane is trimmed straight and level at a true airspeed of 50 m/s at sea level. A pull of 5 N is required to hold a speed of 70 m/s without re-trimming. What would the force and direction required at s speed of 40 m/s without re-trimming? Hint - look at Equations 9.52 and 9.53 in the text. P = A + BV (9.52) 「F-14 ) (9.53)
An airplane is flying with a constant altitude at a speed of 475 mph in a...
An airplane is flying with a constant altitude at a speed of 475 mph in a direction 25° north of west directly towards its final destination. The airplane then encounters wind blowing at a steady 30 mph in a direction 85° north of east. Yes a. Start by drawing a vector diagram for this situation. Did you draw a diagram? Great! Your diagram might look something like this: Wind New Path Original Path b. If the pilot does not correct...
At 30,000 feet above sea level, atmospheric pressure is only 224 torr. That’s why airplane cabins...
At 30,000 feet above sea level, atmospheric pressure is only 224 torr. That’s why airplane cabins are pressurized. There isn’t enough air for you to breathe outside the plane! If we took a balloon filled to 3.86L at room temperature (21°C) and 0.947 atm, what would its volume be at 30,000 feet above sea level (outside the airplane!) if the temperature also reduced to -35.°C?
Problem: The altimeter of a low-speed Piper Aztec reads 8000ft. A Pitot tube mounted on the...
Problem: The altimeter of a low-speed Piper Aztec reads 8000ft.
A Pitot tube mounted on the wingtip measures a pressure of 1650
lb/ft2 . If the outside air temperature is 500 deg R, What is the
true velocity of the airplane?, What is the equivalent
airspeed?
How did they get the pressure of 2.34e-3 for airspeed in step
4?
(4 Bookmarks) Show all steps: ON Chapter 4, Problem 21P = 1.83x10 E Comment Step 3 of 4 A Calculate the...
2. To measure the speed of an airplane, a narrow strip heater is attached to the...
2. To measure the speed of an airplane, a narrow strip heater is attached to the wing of an airplane 0.01 m from the leading edge. A heat flux of 300 W/m²is electrically dissipated and the temperature difference between the heater and the surrounding air is measured to be 1 °C. Assume that the temperature of the wing is uniform. What is the speed of the aircraft? (Hint: Nux = 0.332Rex?Pr1/3) 1q" - 300 W/m² 0.01m Heater Properties of air...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow just outside the boundary layer if the freestream speed Vo = 120 m/s? • What is the local Mach number at this point if the altitude is 12 km? • What is the approximate value of C, for these conditions? Ans: V = 204.35 m/s, M = 0.693, CL ~ 1.15. -1.00 .. .... -0.50 .... ..... 0 0.1 0.2 0.3 0.4 0.5 0.6...
temperature is standard 223k
(b) Consider an airplane flying at an altitude of 10,000m. Assume atmospheric conditions from the standard atmosphere tables in the text. If the stagnation pressure measured by a pitot tube is po = 0.7929 atm, determine the Mach number of the vehicle. Also determine the air speed of the vehicle.
(a) A high speed (Mach number > 0.3) aircraft is flying at an altitude where the temperature and pressure is 2°C and 97 kPa. Its flight velocity is measured by a probe which records a dynamic pressure of 20 density is 13600 kg/ml. Find the reading of the manometer given k=1.4 and R=0.287 kJ/kg-K.
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa and measured (stagnation) temperature of 500 K. DISCUSSION: Suppose that, instead of assuming that a normal shock occurs upstream of the Pitot tube, it is assumed that the flow upstream is ISENTROPIC... what would the estimated flow speed be in that case? (NOTE: A normal shock is always observed to form upstream of bluff bodies such as...
2. (4) An airplane is trimmed straight and level at a true airspeed of 50 m/s at sea level. A pull of 5 N is required to hold a speed of 70 m/s without re-trimming. What would the force and direction required at s speed of 40 m/s without re-trimming? Hint - look at Equations 9.52 and 9.53 in the text. P = A + BV (9.52) 「F-14 ) (9.53)
An airplane is flying with a constant altitude at a speed of 475 mph in a direction 25° north of west directly towards its final destination. The airplane then encounters wind blowing at a steady 30 mph in a direction 85° north of east. Yes a. Start by drawing a vector diagram for this situation. Did you draw a diagram? Great! Your diagram might look something like this: Wind New Path Original Path b. If the pilot does not correct...
Problem: The altimeter of a low-speed Piper Aztec reads 8000ft.
A Pitot tube mounted on the wingtip measures a pressure of 1650
lb/ft2 . If the outside air temperature is 500 deg R, What is the
true velocity of the airplane?, What is the equivalent
airspeed?
How did they get the pressure of 2.34e-3 for airspeed in step
4?
(4 Bookmarks) Show all steps: ON Chapter 4, Problem 21P = 1.83x10 E Comment Step 3 of 4 A Calculate the...
2. To measure the speed of an airplane, a narrow strip heater is attached to the wing of an airplane 0.01 m from the leading edge. A heat flux of 300 W/m²is electrically dissipated and the temperature difference between the heater and the surrounding air is measured to be 1 °C. Assume that the temperature of the wing is uniform. What is the speed of the aircraft? (Hint: Nux = 0.332Rex?Pr1/3) 1q" - 300 W/m² 0.01m Heater Properties of air...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow just outside the boundary layer if the freestream speed Vo = 120 m/s? • What is the local Mach number at this point if the altitude is 12 km? • What is the approximate value of C, for these conditions? Ans: V = 204.35 m/s, M = 0.693, CL ~ 1.15. -1.00 .. .... -0.50 .... ..... 0 0.1 0.2 0.3 0.4 0.5 0.6...
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