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• ## PollSupersonic flow has a Mach number

Supersonic flow has a Mach number

Asked on 29th June 2020 in
• 281 views
• ## Calculate the percentage of the profile drag coefficient that is due to pressure drag.

The airfoil section of a wing is an NACA 2213 at the wing root, tapering to an NACA 2205  at …

Asked on 18th February 2019 in
• 2K views

The temperature and pressure at the stagnation point of a high speed missile are $${934^ \circ }$$ R and 7.8 atm, …

Asked on 26th December 2018 in
• 1K views
• ## Calculate velocity on the airfoil.

Calculate the velocity at a point on the airfoil, where the pressure is $${\rm{0}}{\rm{.4 \times 1}}{{\rm{0}}^{\rm{5}}}{\rm{N/}}{{\rm{m}}^{\rm{2}}}$$. The free stream velocity …

Asked on 28th December 2018 in
• 1K views
• ## What will be the pressure at downstream of the streamline.

In an inviscid, incompressible flow of air along a streamline, the air density is 0.002377 $${\rm{slug/f}}{{\rm{t}}^{\rm{3}}}$$. At a point on …

Asked on 28th December 2018 in
• 830 views
• ## Find circulations around the cylinder.

Lift per unit span of a spinning circular cylinder in a free stream with velocity  of 50 m/s is 8 …

Asked on 28th December 2018 in
• 771 views
• ## How to find locations on the surface of the cylinder for the following.

Calculate locations on the surface of a cylinder where surface pressure equals to free-stream pressure considering a non-lifting flow.

Asked on 29th December 2018 in
• 709 views

Consider a non-lifting flow over a circular cylinder and derive an expression for the pressure coefficient at any arbitrary point $$\left( … Asked on 29th December 2018 in • 716 views • 1 answers • 0 votes • ## Explain if there is any change in the shape of streamlines. Consider the non lifting flow over a circular cylinder of a given radius, where free stream velocity is \({V_\infty }$$.If \({V_\infty …

Asked on 29th December 2018 in
• 649 views