Kumar59's Profile

331
Points

Questions
27

67

• ## 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 temperature are $$200\,m/s$$, $$1\,atm$$ and $$300\,K$$. 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 …

Kumar59 Asked on 13th January 2022 in
• 506 views
• ## What is the difference between inertial navigation system (INS) and inertial reference system (IRS) in aviation?

What is the difference between inertial navigation system (INS) and inertial reference system (IRS) in aviation?

Kumar59 Asked on 13th December 2021 in
• 621 views
• ## What are form drag and profile drag?

What are form drag and profile drag?

Kumar59 Asked on 8th September 2021 in
• 852 views
• ## What are the roles of ailerons and flaps in an aircraft?

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

Kumar59 Asked on 7th September 2021 in
• 737 views
• ## 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 $$6^{\circ}$$.

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

Kumar59 Asked on 11th August 2021 in
• 557 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 …

Kumar59 Asked on 16th June 2021 in
• 569 views
• ## Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of venturi is $$100 000 N/m^{2}$$.

Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of …

Kumar59 Asked on 15th June 2021 in
• 642 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 … Kumar59 Asked on 5th May 2021 in • 715 views • 1 answers • 0 votes • ## A velocity field is given by \(u=\frac{y}{x^{3}+y^{3}}$$ and $$v=\frac{-x}{x^{3}+y^{3}}$$. Find its 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.

Kumar59 Asked on 15th April 2021 in
• 669 views
• ## Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $$8^{\circ}$$ in a Mach $$3$$ flow.
Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of $$8^{\circ}$$ …