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Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach $2.5$ freestream flow at an angle of attack of $5^{^{\circ}}$ , using linearized theory.
Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach $2.5$ freestream flow …
Aircraft performance

drag coefficient

lift and drag

Supersonic airplanes

Worldtech Asked on 27th January 2022 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Why is critical Mach number of a sphere higher than a cylinder?
Why is critical Mach number of a sphere higher than a cylinder?
Airplane design

airspeed

Mach number

Kisan Kumar Asked on 13th January 2022 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
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
An airfoil is in airflow with $0.52$ free stream Mach number. Local Mach number at a given point is $0.82$ . 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 $0.82$ . …
airfoil

airspeed

Compressible flow

Mach number

Worldtech Asked on 13th January 2022 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
What are stagnation pressure and stagnation temperature?
What are stagnation pressure and stagnation temperature?
airspeed

Worldtech Asked on 7th September 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
A circular cylinder and a sphere are in a free stream flow with their axis perpendicular to the flow. At the top of the sphere there is a pressure tap which is connected by a tube to one side of a manometer. There is a pressure tap on the surface of the cylinder which is connected to the other side of the manometer. Find the location of this tap on cylindrical surface such that there is no deflection of fluid in the manometer.
A circular cylinder and a sphere are in a free stream flow with their axis perpendicular to the flow. At …
fluids

incompressible flow

Kisan Kumar Asked on 1st September 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
A NACA 4421 airfoil having a chord length of $2\,m$ is flying at an velocity of $70\,m/s$ at an altitude of $2\,km$ . 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 …
airfoil

airspeed

Circulation

lift coefficient

Kisan Kumar Asked on 22nd July 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
An airfoil has a lift coefficient and moment coefficient of $-0.35$ and $-0.050$ about quarter-chord at $-6^{\circ}$ angle of attack. The airfoil has lift coefficient and moment coefficient of $0.70$ and $-0.040$ at an angle of attack of $4^{\circ}$ about the same quarter chord. Find the location of the aerodynamic center.
An airfoil has a lift coefficient and moment coefficient of $-0.35$ and $-0.050$ about quarter-chord at $-6^{\circ}$ angle of attack. …
aerodynamic center

airfoil

lift coefficient

techAir Asked on 22nd July 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Can an airfoil fly upside-down ?
A positively cambered airfoil has a zero-lift angle of $-3.5^{\circ}$ . The lift slope for this airfoil is $0.12$ per degree. …
airfoil

lift

lift and drag

lift coefficient

lift force

Kisan Kumar Asked on 13th July 2021 in Aerodynamics.
- 3K 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

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