Kumar59's Profile

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63

• ## What are form drag and profile drag ?

What are form drag and profile drag ?

Asked on 8th September 2021 in
• 12 views
• ## What are the roles of ailerons and flaps in an aircraft?

What are the roles of ailerons and flaps in an aircraft?

Asked on 7th September 2021 in
• 53 views
• ## Find the coefficient of lift and induced drag coefficients for this wing at an angle of attack of $$6^{\circ}$$.

A finite wing has aspect ratio of $$6$$ and taper ratio of $$0.8$$. The airfoil constituting this wing has a …

Asked on 11th August 2021 in
• 112 views
• ## Find the circulation around a spinning circular cylinder in free stream flow of velocity $$40\,m/s$$ at a standard sea level conditions, if the lift produced by the cylinder is $$8\,N/m$$ of span.

Find the circulation around a spinning circular cylinder in free stream flow of velocity $$40\,m/s$$ at a standard sea level …

Asked on 16th June 2021 in
• 123 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 $$0.8$$.  …

Asked on 15th June 2021 in
• 127 views

A velocity field is given by $$V=3yt\hat{i}+5x\hat{j}$$. Find the equation of the streamline passing through the point $$(5,3)$$ at $$t … Asked on 5th May 2021 in • 265 views • 1 answers • 0 votes • ## Find the vorticity. A velocity field is given by \(u=\frac{y}{x^{3}+y^{3}}$$ and $$v=\frac{-x}{x^{3}+y^{3}}$$. Find its vorticity.

Asked on 15th April 2021 in
• 149 views
• ## Find the lift and wave drag coefficients for an infinitely thin flat plate.

Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $$8^{\circ}$$ …

Asked on 26th March 2021 in
• 137 views
• ## Find the wave angle, downstream Mach number, pressure and temperature.

A flow is passing over a $${20^ \circ }$$ half-angle wedge having a upstream Mach number, pressure and temperature of …

Asked on 11th March 2021 in
• 141 views
• ## Find $${P_2},{T_2},\,{\rho _2},\,{M_2},{P_{02}}$$ and $${T_{02}}$$ downstream of the shock wave.
A flow passes through a normal shock wave has a pressure, temperature and Mach number of  $$1\,atm,\,295\,K$$ and $$2.8$$ upstream …