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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 …
airspeed

Compressible flow

Kumar59 Asked on 13th January 2022 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
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?
aircraft instrument

Kumar59 Asked on 13th December 2021 in Technology.
- 1K views
- 1 answers
- 0 votes
What are form drag and profile drag?
What are form drag and profile drag?
drag

drag coefficient

drag force

lift and drag

Kumar59 Asked on 8th September 2021 in Aeronautics.
- 2K views
- 1 answers
- 0 votes
What are the roles of ailerons and flaps in an aircraft?
What are the roles of ailerons and flaps in an aircraft?
Aircraft performance

Kumar59 Asked on 7th September 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
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 …
airfoil

Induced drag

lift coefficient

Kumar59 Asked on 11th August 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
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 …
Circulation

lift

Kumar59 Asked on 16th June 2021 in Aerodynamics.
- 1K 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 $100 000 N/m^{2}$ .
Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of …
airspeed

incompressible flow

Kumar59 Asked on 15th June 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
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 $t =3$ . Units of $x,y$ are in meters and time- $t$ is in seconds.
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 …
fluids

streamlines

Kumar59 Asked on 5th May 2021 in Fluid mechanics.
- 1K 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.
Vorticity

Kumar59 Asked on 15th April 2021 in Fluid dynamics.
- 1K views
- 1 answers
- 0 votes
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 $8^{\circ}$ …
drag coefficient

lift and drag

lift coefficient

Supersonic airplanes

Supersonic flow

Kumar59 Asked on 26th March 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes

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