If lift coefficient at thrust required minimum is 0.85 and induced drag factor K is 0.0085 then, find the approximate value of drag coefficient at zero lift.

If lift coefficient at thrust required minimum is 0.85 and induced dr

1.	If lift coefficient at thrust required minimum is 0.85 and induced drag factor K is 0.0085 then, find the approximate value of drag coefficient at zero lift.
A.	0.0061
B.	0.061
C.	0.61
D.	6.1
Answer» B. 0.061

Discussion

No Comment Found

Related MCQs

Find the drag at which thrust required is minimum. Consider CD0 as 0.015 and reference area is 5m2. Consider steady level flight with q of 15Pa.
Which of the following is required condition of thrust required minimum?
If lift coefficient at thrust required minimum is 0.85 and induced drag factor K is 0.0085 then, find the approximate value of drag coefficient at zero lift.
Find the velocity for minimum thrust required at steady level flight if wing loading is 75N/m2 and induced drag factor K is 0.0025. Consider CD0 as 0.02 and density as sea level.
We can design our aircraft to cruise for 3 different lift to drag ratio. Lift to drag ratio are as follows: 10, 12 and 11.25. Now, if we want to reduce thrust required to fly then, at which value of lift to drag ratio our aircraft needs to be designed so that it can operate with minimum thrust required?
Let’s consider our aircraft has to generate thrust of 150KN during cruise. If at the cruise thrust loading is 0.86 then, at which value of Lift our aircraft is flying?
An aircraft is designed to be in steady level flight with weight of 1500N and CL of 1.0. Determine at which speed we need to design this aircraft so that it can achieve this requirement. Consider density as 1.2 kg/m3 and reference area as 2m2.
If an aircraft is in steady level flight and weighs 2500 kg then, find lift at the given flight condition.
An aircraft is designed with lift coefficient of 1.1 during steady level flight. If dynamic pressure is set to be 25.65 Pa then find weight of aircraft during this flight condition.
An aircraft has to be designed to operate at aerodynamic efficiency of 10 at cruise. Find the required thrust to weight ratio for maintaining this unaccelerated steady level flight.

If lift coefficient at thrust required minimum is 0.85 and induced drag factor K is 0.0085 then, find the approximate value of drag coefficient at zero lift.

Discussion

No Comment Found

Related MCQs

Reply to Comment