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Latest
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Worldtech
An airfoil is in airflow with
0.52
free stream Mach number. Local Mach number at a given point is
0.82
. Find the pressure coefficient at this point.
airfoil
airspeed
Compressible flow
Mach number
on 13th January 2022 in
Aerodynamics.
1K
1
0
Worldtech
A finite wing with an elliptical lift distribution has an aspect ratio of
6
. The airfoil of the wing has a lift slope of
0.15
per degree. Find and compare the lift slopes for a straight wing and a swept wing with a half-chord line sweep of
30^{\circ}
.
airfoil
lift coefficient
swept wing
on 12th August 2021 in
Aeronautics.
1K
1
0
techAir
An airplane is cruising at
50\,m/s
at standard sea level in straight and level flight. The airplane has a wing area of
15\,m^2
and a wing span of
10\,m
, and has the maximum gross weight of
1000\,kg
. The airfoil of the wing has lift slope of
0.102
per degree and angle of attack at zero lift of
-2.5^{\circ}
. Considering,
\tau = 0.1
, find the angle of attack for the wing. Also, find the induced drag for the airplane, if span efficiency factor is
0.6
.
Aircraft performance
airfoil
Induced drag
on 12th August 2021 in
Aeronautics.
1K
1
0
Kumar59
A finite wing has aspect ratio of
6
and taper ratio of
0.8
. The airfoil constituting this wing has a lift slope of
0.102
per degree, and angle of attack at zero lift of
-1.2^{\circ}
. Assuming that
\delta =\tau
and equals approximately
0.03
, find the coefficient of lift and induced drag coefficients for this wing at an angle of attack of
6^{\circ}
.
airfoil
Induced drag
lift coefficient
on 11th August 2021 in
Aeronautics.
1K
1
0
Kisan Kumar
A NACA 4421 airfoil having a chord length of
2\,m
is flying at an velocity of
70\,m/s
at an altitude of
2\,km
. Find the lift per unit span and the circulation at an angle of attack of
4^{\circ}
, for this airfoil.
airfoil
airspeed
Circulation
lift coefficient
on 22nd July 2021 in
Aerodynamics.
1K
1
0
techAir
An airfoil has a lift coefficient and moment coefficient of
-0.35
and
-0.050
about quarter-chord at
-6^{\circ}
angle of attack. The airfoil has lift coefficient and moment coefficient of
0.70
and
-0.040
at an angle of attack of
4^{\circ}
about the same quarter chord. Find the location of the aerodynamic center.
aerodynamic center
airfoil
lift coefficient
on 22nd July 2021 in
Aerodynamics.
2K
1
0
Worldtech
A NACA 0012 airfoil having a chord of
2.3\,m
is in an airstream velocity of
70\,m/s
at standard sea level conditions. Find the angle of attack for this airfoil, if the lift per unit span produced is
1400\,N
.
airfoil
airspeed
lift
lift coefficient
lift force
on 22nd July 2021 in
Aeronautics.
1K
1
0
Kisan Kumar
Can an airfoil fly upside-down ?
airfoil
lift
lift and drag
lift coefficient
lift force
on 13th July 2021 in
Aerodynamics.
3K
1
0
Kumar59
Find the coefficient of pressure at a point on the wing where the velocity is
58\,m/s
. The airplane is flying at a low speed of
50\,m/s
.
Aircraft performance
airfoil
Airplane design
on 14th January 2021 in
Flight mechanics.
2K
1
0
Kisan Kumar
Calculate the pressure coefficient at a point on the airfoil where the pressure is
8.9 \times 10^4\,N/m^2
. Airfoil is in freestream velocity of
40\,m/s
and is at standard sea – level conditions.
Aircraft performance
airfoil
Airplane design
on 12th January 2021 in
Aeronautics.
2K
1
0
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