# Problems a jet airplane has the ta (attachment)

5. A jet airplane has the TA
and TR curves in fig. 2-1. The airplane data: weight = 12,000 lb.
standard sea level day; clean configuration. Find:

a. Vmax at
95%

b.
V for maximum climb angle 95% (RPM)

c.
sine of maximum climb angle (100% RPM)

d.
Rate of climb at 300 knots (95% RPM)

e.
V for best endurance;

f.
Vfor maximum range;

g.
V for maximum range with 100 knots of headwind.

h.
The value of L/D max

Home Work #6

3.
How much horsepower does it take to climb a 4000 pound airplane through a 1980
foot change in altitude in one minute?

.
In a power off glide at 78 knots, the drag is 200 pounds. In a 2450
pound aircraft, what is the rate of descent?

5.
If 500 pounds of thrust results in 200 knots TAS, what is the thrust
horsepower?

What is the brake horsepower assuming 88% propeller efficiency?

6.
At 5500 ft density altitude and 55% Power, a B-19 consumes 6.7 gallons per hour
in order to generate 84 knots true airspeed. What is the specific range?

7.
A Travel Air uses 16 gallons per hour to generate 234HP. What is the specific
fuel consumption?

11. Using figure 2-2 Calculate the
velocity for best range with a 100kt headwind for the airplane at 12,000 and
8,000 lb gross weight.

15. Using
the PA-PR curves in 2-3 for a propeller airplane find: (Assume a
10,000-lb weight)

a.
Vmax

b.
sine of the climb angle at Vs

c.
sine of the climb angle at L/D max

d.
rate of climb at Vs

e.
rate of climb at 300 knots

f.
velocity for maximum endurance

g.
velocity for maximum range

h. velocity for maximum range

19.
A Beech Baron 55 has a published sea level power of 520 HP. At 10,000
feet with 70% cruise power set, the fuel flow is 30 gallons per hour and the
TAS is 200 knots.

What
is the specific fuel consumption?_______

What
is the Specific range?________

22. How much brake horsepower does
it take to cruise an airplane under the following conditions?

Drag
= 600
lbs

IAS
= 200
kts

Density
ratio =
..7385

Propeller
efficiency = 80%

23. It requires 525 pounds
of thrust to hold 200 knots EAS at sea level. How much thrust would it take to
hold the same EAS at 15,000 feet?

hint: in balanced flight drag equals
thrust required

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