The temperature varies linearly from sea level to approximately 11 km altitude in the standard atmosphere. Evaluate the lapse rate —the rate of decrease of temperature with altitude—in the standard atmosphere. Derive an expression for the rate of change of sonic speed with altitude in an ideal gas under standard atmospheric conditions. Evaluate and plot the sonic speed from sea level to 10 km altitude.
The temperature varies linearly from sea level to approximately 11 km altitude in the standard atmosphere. Evaluate the lapse rate —the rate of decrease of temperature with altitude—in the standard atmosphere. Derive an expression for the rate of change of sonic speed with altitude in an ideal gas under standard atmospheric conditions. Evaluate and plot the sonic speed from sea level to 10 km altitude.
The temperature varies linearly from sea level to approximately 11 km altitude in the standard atmosphere. Evaluate the lapse rate—the rate of decrease of temperature with altitude—in the standard atmosphere. Derive an expression for the rate of change of sonic speed with altitude in an ideal gas under standard atmospheric conditions. Evaluate and plot the sonic speed from sea level to 10 km altitude.
On October 3, 1967, pilot William J. "Pete" Knight set a world record that still stands to this day for the fastest flight by a crewed, powered aircraft by flying the North American Aviation X-15 as fast as Mach 6.7 at an altitude of 102,000 ft above sea level. Mach number is the ratio of an object’s velocity to the local speed of sound. Using the table for atmospheric properties with respect to altitude, calculate the speed of sound at an altitude of 100,000 ft. What must have been the velocity of the X-15?
5. At 30000ft, estimate the magnitude of transonic drag rise. Using this estimate,
calculate the maximum velocity of the airplane at this altitude. Assume drag-divergence
Mach number of 0.82 and d(D/D₁)/dM = 14.3 where D₁=1750lb is drag at Mach number
0.9 and D₂ = 4250lb at Mach number 1.
6 Estimate maximum range at 30000€ Also calculate the flight speed to obtain this
A jet aircraft weighs 150,000 N and has a wing area of 30 m2. Its drag polar
is given by Cp = 0.015 +0.025C. The sea level thrust To is equal to 23,200 N,
and the thrust at altitude is given by T = Too. The specific fuel consumption at sea
level co is 1.2 N/Nh and, at altitude, c = coo. Determine (a) the most economical
cruise altitude and (b) fuel load and cruise velocity for a Breguet range of 2500 km.
[Answer: (a) 12.31 km and (b) 6030.0 N and 205.166 m/s.]
Chapter 12 Solutions
Fox and McDonald's Introduction to Fluid Mechanics
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