Drag Polar Equation: Cd=0.0018+0.05CL2 Altitude: 1,000 m & 8,000 m Mass: 25,000 kg & 30,000 kg Reference Area (m2 ): 80
Posted: Tue Apr 26, 2022 4:52 pm
Drag Polar
Equation: Cd=0.0018+0.05CL2
Altitude: 1,000 m & 8,000 m
Mass: 25,000 kg & 30,000 kg
Reference Area (m2 ): 80
a) Calculate thrust required values at least 5 different
velocities between 0.3 and 0.8 Mach at two different altitudes and
for two different aircraft weights. Draw these four curves on the
same graph and show the calculated points on the curves. You can
use excel or Matlab software to make your calculations and draw the
graphs. If you prefer to draw the graphs by your hand, you need to
use millimeter paper.
b) Calculate the maximum lift to drag ratio
(L/D)max of your aircraft. Calculate lift to drag
ratio for two different aircraft weights at two different altitudes
to be able to fly steadily at 0.5 Mach velocity. Compare these
results and make comments about the angles of attacks of these
conditions.
c)Assume that your aircraft is powered by a turbojet engine and
its maximum thrust at sea level is 120 kN. Calculate the maximum
speeds of two different weights of aircraft for two different
altitudes. Compare the results and comment on the effects of weight
and altitude on the reachable maximum speed of your aircraft.
d)Calculate the available power of your turbojet aircraft which
is given in the previous question using at least 5 different
velocities between 0.3 and 0.8 Mach at lower altitudes and smaller
weight conditions.
Calculate power required values for the same aircraft at the
same altitude at the same speeds that you have already calculated.
Show all calculated values on the same graph. Use different markers
for available power and required power points to see their behavior
of them with respect to velocity. You can use excel or Matlab
software to make your calculations and draw the graphs. If you
prefer to draw the graphs by your hand, you need to use millimeter
paper.
Equation: Cd=0.0018+0.05CL2
Altitude: 1,000 m & 8,000 m
Mass: 25,000 kg & 30,000 kg
Reference Area (m2 ): 80
a) Calculate thrust required values at least 5 different
velocities between 0.3 and 0.8 Mach at two different altitudes and
for two different aircraft weights. Draw these four curves on the
same graph and show the calculated points on the curves. You can
use excel or Matlab software to make your calculations and draw the
graphs. If you prefer to draw the graphs by your hand, you need to
use millimeter paper.
b) Calculate the maximum lift to drag ratio
(L/D)max of your aircraft. Calculate lift to drag
ratio for two different aircraft weights at two different altitudes
to be able to fly steadily at 0.5 Mach velocity. Compare these
results and make comments about the angles of attacks of these
conditions.
c)Assume that your aircraft is powered by a turbojet engine and
its maximum thrust at sea level is 120 kN. Calculate the maximum
speeds of two different weights of aircraft for two different
altitudes. Compare the results and comment on the effects of weight
and altitude on the reachable maximum speed of your aircraft.
d)Calculate the available power of your turbojet aircraft which
is given in the previous question using at least 5 different
velocities between 0.3 and 0.8 Mach at lower altitudes and smaller
weight conditions.
Calculate power required values for the same aircraft at the
same altitude at the same speeds that you have already calculated.
Show all calculated values on the same graph. Use different markers
for available power and required power points to see their behavior
of them with respect to velocity. You can use excel or Matlab
software to make your calculations and draw the graphs. If you
prefer to draw the graphs by your hand, you need to use millimeter
paper.