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Why is critical Mach number of a sphere higher than a cylinder ?
Why is critical Mach number of a sphere higher than a cylinder ?
Airplane design

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Mach number

Kisan Kumar Asked 4 days ago in Aerodynamics.
- 11 views
- 0 answers
- 0 votes
Find the velocity, pressure and temperature at, \((0.07\,m, 0.07\,m)\).
Velocity potential of a subsonic compressible flow is \[\phi(x,y) = V_{\infty}x + \frac{5}{\sqrt{1 – M_{\infty}^{2}}}e^{-2\pi\sqrt{1-M_{\infty}^{2}}y}sin2\pi x\] Freestream velocity, pressure and …
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Compressible flow

Kumar59 Asked 4 days ago in Aerodynamics.
- 13 views
- 0 answers
- 0 votes
Find the pressure coefficient at this point.
An airfoil is in airflow with \(0.52\) free stream Mach number. Local Mach number at a given point is \(0.83\). …
airfoil

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Compressible flow

Mach number

Worldtech Asked 4 days ago in Aerodynamics.
- 11 views
- 0 answers
- 0 votes
What are stagnation pressure and stagnation temperature ?
What are stagnation pressure and stagnation temperature ?
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Worldtech Asked on 7th September 2021 in Aerodynamics.
- 302 views
- 1 answers
- 0 votes
Find the lift per unit span and the circulation at an angle of attack of \(4^{\circ}\), for this airfoil.
A NACA 4421 airfoil having a chord length of \(2\,m\) is flying at an velocity of \(70\,m/s\) at an altitude …
airfoil

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Circulation

lift coefficient

Kisan Kumar Asked on 22nd July 2021 in Aerodynamics.
- 212 views
- 1 answers
- 0 votes
Find the angle of attack for this airfoil, if the lift per unit span produced is \(1400\,N\).
A NACA 0012 airfoil having a chord of \(2.3\,m\) is in an airstream velocity of \(70\,m/s\) at standard sea level …
airfoil

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lift

lift coefficient

lift force

Worldtech Asked on 22nd July 2021 in Aeronautics.
- 236 views
- 1 answers
- 0 votes
An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of the wing where the flow velocity is \(140\,m/s\).
An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of …
Aircraft performance

Airplane design

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Worldtech Asked on 16th June 2021 in Aerodynamics.
- 201 views
- 1 answers
- 0 votes
A pitot tube of an airplane which is flying at an standard sea level measures a pressure of \(1.09 \times 10^{5} N/m^{2}\). Find the velocity of the airplane.
A pitot tube of an airplane which is flying at an standard sea level measures a pressure of \(1.09 \times …
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incompressible flow

techAir Asked on 16th June 2021 in Aerodynamics.
- 215 views
- 1 answers
- 0 votes
Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has an inlet -to-throat area ratio of \(10\).
Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has …
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incompressible flow

Kisan Kumar Asked on 15th June 2021 in Aeronautics.
- 203 views
- 1 answers
- 0 votes
Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of venturi is \(100 000 N/m^{2}\).
A venturi is attached on a side of an airplane fuselage, has an throat to inlet area ratio of \(0.8\). …
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incompressible flow

Kumar59 Asked on 15th June 2021 in Aerodynamics.
- 202 views
- 1 answers
- 0 votes

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