2. An airplane has a mass of 50,000 kg, a wing area of 300m², a maximum lift coefficient of 3.2, and cruising drag coefficient of 0.03 at an altitude of 12,000m. Determine (a) the takeoff speed at sea level; assuming it is 20 percent more than the stall speed, and (b) the thrust that the engines must deliver for a cruising speed of 700km/h. And part B. ((@on) = 1.285 P (@1000) = 0.312 kg/m³ a./ take-off = 1.2x Ustall 0 power for (Ustall is U at which = wight • Lift fire) by Fr =
2. An airplane has a mass of 50,000 kg, a wing area of 300m², a maximum lift coefficient of 3.2, and cruising drag coefficient of 0.03 at an altitude of 12,000m. Determine (a) the takeoff speed at sea level; assuming it is 20 percent more than the stall speed, and (b) the thrust that the engines must deliver for a cruising speed of 700km/h. And part B. ((@on) = 1.285 P (@1000) = 0.312 kg/m³ a./ take-off = 1.2x Ustall 0 power for (Ustall is U at which = wight • Lift fire) by Fr =
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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and power for part b
Transcribed Image Text:2. An airplane has a mass of 50,000 kg, a wing area of 300m², a maximum lift coefficient of 3.2, and
cruising drag coefficient of 0.03 at an altitude of 12,000m. Determine (a) the takeoff speed at sea level;
assuming it is 20 percent more than the stall speed, and (b) the thrust that the engines must deliver for
a cruising speed of 700km/h. And
part B.
((@on)
= 1.285
P (@1000) = 0.312 kg/m³
a./ take-off = 1.2x Ustall
0
power
for
(Ustall is
U at which
=
wight • Lift fire)
by Fr
=
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