# For the following problems, consider a single-engine jet airplane with the following characteristics:Weight: 32,000 lbsWing span: 65 ftAspect ratio: 7Oswald efficiency: 0.8Zero-lift drag...

For the following problems, consider a single-engine jet airplane with the following characteristics:

Weight: 32,000 lbs
Wing span: 65 ft
Aspect ratio: 7
Oswald efficiency: 0.8
Zero-lift drag coefficient: 0.0270
Maximum lift coefficient: 1.3 with flaps up
Engine: one JT8D without afterburner, based on the engine deck provided with Mini-Project 2

Presume that a two-parameter quadratic drag polar is appropriate, and do not model wave drag.

1. Plot a skymap showing contours of maximum climb rate in ft/min. Trim the skymap with a stall constraint and a P

s, max

= 0 constraint using hatched lines, and display the climb rate contours only within the feasible flight envelope. Compute the path on the skymap that results in the minimum time to climb to a given altitude for altitudes up to the aircraft’s absolute ceiling. The resulting plot should be similar to the plot shown on slide 13 of the climb lecture notes. Comment on the features of the plot.

2. Presume that the engine fails at an altitude of 10,000 ft and the airplane begins gliding flight.

1. Make a plot of glide range in nautical miles vs. airspeed in knots for the glide. What is the optimum speed to maximize glide range?

2. Make a plot of time aloft in minutes vs. airspeed in knots for the glide. What is the optimum speed to maximize time aloft in glide?

3. Are either of the optimum speeds less than the level flight stall speed, implying that the airplane must glide at a faster speed to avoid stall?

3. Consider the airplane at 10,000 ft altitude and presume that the airplane is certificated to a limit load factor of 3.5 g’s.

1. Plot a V-n diagram envelope showing the positive-n structural limit, stall limit, and a never-exceed speed of 300 knots.

2. What is the cornering speed in knots?

3. What is the level turn radius in feet and turn rate in deg/min at the cornering speed?

4. Plot the curve corresponding to maximum load factor associated with maximum

engine thrust for a level, constant speed turn.

Answered 4 days AfterApr 14, 2023

## Answer To: For the following problems, consider a single-engine jet airplane with the following...

Karthi answered on Apr 18 2023
Jet
For the following problems, consider a single-engine jet airplane with the following
characteristics:
Weight: 32,000 lbs
Wing span: 65 ft
Aspect ratio: 7
Oswald efficiency: 0.8
Zero-lift
drag coefficient: 0.0270
Maximum lift coefficient: 1.3 with flaps up
Engine: one JT8D without afterburner, based on the engine deck provided with Mini-Project 2
Presume that a two-parameter quadratic drag polar is appropriate, and do not model wave drag.
Plot a skymap showing contours of maximum climb rate in ft/min. Trim the skymap with a stall
constraint and a P
s, max
= 0 constraint using hatched lines, and display the climb rate contours only within the feasible
flight envelope. Compute the path on the skymap that results in the minimum time to climb to a
given altitude for altitudes up to the aircraft’s absolute ceiling. The resulting plot should be similar
to the plot shown on slide 13 of the climb lecture notes. Comment on the features of the plot.
Presume that the engine fails at an altitude of 10,000 ft and the airplane begins gliding flight.
Make a plot of glide range in nautical miles vs. airspeed in knots for the glide. What is the
optimum speed to maximize glide range?
Make a plot of time aloft in minutes vs. airspeed in knots for the glide. What is the optimum
speed to maximize time aloft in glide?
Are either of the optimum speeds less than the level flight stall speed, implying that the airplane
must glide at a faster speed to avoid stall?
To determine if either of the optimum speeds for maximum endurance or maximum range is less
than the level flight stall speed, we need to compute the stall speed of the aircraft.
The stall speed in level flight, Vstall, can be determined using the maximum lift coefficient,
CLmax, and the weight of the aircraft, W, as follows:
Vstall = sqrt((2W)/(rhoSCLmax))
where rho is the air density, S is the wing area, and CLmax is the maximum lift coefficient.
Assuming standard sea level...
SOLUTION.PDF