# 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. V_{max }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 P_{A}-P_{R} curves in 2-3 for a propeller airplane find: (Assume a

10,000-lb weight)

a.

Vmax

b.

sine of the climb angle at V_{s}

c.

sine of the climb angle at L/D max

d.

rate of climb at V_{s}

e.

rate of climb at 300 knots

f.

velocity for maximum endurance

g.

velocity for maximum range

h. velocity for maximum range

with 100 knots headwind

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