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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 ?

• 11 views
• ## 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 …

• 13 views
• ## 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 $$0.83$$. …

• 11 views
• ## What are stagnation pressure and stagnation temperature ?

What are stagnation pressure and stagnation temperature ?

Asked on 7th September 2021 in
• 302 views
• ## 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 …

Asked on 22nd July 2021 in
• 212 views
• ## 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 …

Asked on 22nd July 2021 in
• 236 views
• ## 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 …

Asked on 16th June 2021 in
• 201 views

A pitot tube of an airplane which is flying at an standard sea level measures a pressure of $$1.09 \times … Asked on 16th June 2021 in • 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 …

Asked on 15th June 2021 in
• 203 views
• ## 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 $$0.8$$.  …