Aero242 EXAM 2 S99
Name ____________________
- The following aircraft characteristics, and density relation are to
be used for all problems.
- Present equations used, followed by values substituted in, and final answer.
| Wingspan |
53.3 ft |
|
|
| Wing area |
318 sq ft |
|
|
| Gross T/O Weight |
19815 lb |
|
|
| Fuel Capacity |
1119 gal
1 gal jet fuel weighs 6.67 lb |
|
|
| Power Plant |
2 turbofans
3650 lb thrust each @ MSL |
|
|
| TSFC |
0.60 lb/lb-hr |
|
|
| CDo |
0.020 |
|
|
| e |
0.81 |
|
|
| mu (take-off) | 0.02 |
| mu (landing) | 0.4 |
| CLmax (partial flaps ontake-off) |
1.8 |
| CL (take-off) |
.2 |
| CLmax (full flaps on approach) |
2.5 |
| CL (with spoilers) |
0 |
| TR (no thrust reversers) |
0 |
density at sea level = 0.0023769 slugs/cu ft
density at 40000 ft altitude = 0.00058727 slugs/cu ft
otherwise,
density=0.0023769*0.29709*exp((36000.-h)/20786.)
- What is the takeoff lift-off distance at sea-level (integrated method)?
- The aircraft begins a cruise-climb at 40,000 ft with 1000 gallons of fuel
on board. How far can it go and have 50 gallons left to begin descent to landing?
- At 1000 ft altitude (assume sea-level atmospheric conditions),
the aircraft is out of fuel and flies so as to achieve a maximum glide distance to the
runway.
- What is its angle of se