1. (25 points) Calculate air pressure, temperature, density, and local speed of sound for altitudes
of 18,000 and 35,000 feet. Assume International Standard Atmosphere (ISA) for the standard
troposphere with the STLR= -0.0065 K/m = -2 K/1000 ft = -2o C/1000 ft, and with the standard
S.L. conditions

 

2. (25 points) A B767-300ER is flying at 265 KIAS (indicated airspeed) at 18,000 feet MSL and
at 33,000 feet. Calculate the Mach (M) numbers the B767 is flying at 18,000 and 33,000 feet
assuming the ISA (International Standard Atmosphere) conditions. Assume IAS=CAS=EAS
(No calibration and no Pitot compressibility error). The isentropic coefficient for air is γ=1.4
and the air gas constant R is 287 J/kg K.

 

3. (25 points) Estimate zero-wind lift-off (ground) distance for the Citation corporate jet at the
maximum takeoff weight (MTOW) of 20,000 lbs at elevation of 4,000 feet in ISA conditions.
Wing surface area is 320 ft 2 . Assume liftoff speed is 15% above the stalling speed in takeoff
configuration. Assume zero-wind conditions (GS=TAS). Due to required ground clearance on
rotation and the tail-strike possibility the maximum lift-off coefficient of lift is 1.75 with flaps
in takeoff configuration. Maximum takeoff thrust is 7,000 lbs and is constant during the takeoff
run and liftoff. Runway is perfectly flat (zero slope). Assume average aerodynamic and rolling
drag during takeoff roll to be 3,000 lb. What is total (gross or unfactored) takeoff distance, if
the airborne distance to 35 ft height from liftoff is 1,250 ft.

4. (25 points) A Boeing 737-400 large transport-category civilian jet transport weighs 150,000
lbs on takeoff and SL ISA conditions (air density is 0.002377 slug/ft 3 ). The airplane lifts off
and accelerates to takeoff safety speed (V2) of 163 KEAS (assume IAS=CAS=EAS). Two
CFM56 high bypass turbofans produce constant flat-rated 2 x 22,500 lbs of thrust (maximum
takeoff thrust) at given SL ISA altitude. Neglect maximum thrust decrease with altitude.
Airplane's wing reference area is 1,200 ft 2 . The coefficient of drag is 0.085 in the takeoff flap
configuration (with landing gears and doors retracted). Calculate the ROC (rate-of-climb) and
the AOC (angle-of-climb) if both engines are operating and the airplane is flying at V2+15
(smaller AOA than at V2) knots up to 800 ft AGL. What will be ROC (fpm) and AOC (in
radians, percentage, and degrees) in initial climb to 800 ft AGL if one engine fails completely
during takeoff roll just before V1 and the decision is to go. Assume OEI drag coefficient of
0.110 due to the additional higher AOA (at V2), trim drag, and the inoperative jet engine wind-
milling drag (drag due to any sideslip is neglected)? What is percentage loss of climb
performance in OEI case?