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How urban air mobility work?
How urban air mobility work?
Airplane design

flight mechanics

techAir Asked on 13th December 2021 in Aeronautics.
- 1K views
- 1 answers
- 0 votes
What is AWACS?
What is AWACS?
aircraft instrument

Airplane design

Kisan Kumar Asked on 13th December 2021 in Technology.
- 959 views
- 1 answers
- 0 votes
What are the instruments that are present inside an aircraft’s cockpit?
What are the instruments that are present inside an aircraft’s cockpit?
aircraft instrument

Aircraft performance

Airplane design

techAir Asked on 8th November 2021 in Technology.
- 1K views
- 1 answers
- 0 votes
An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of the wing where the flow velocity is \(140\,m/s\).
An airplane is flying at an velocity of \(100\,m/s\). Find the pressure coefficient at a point on the surface of …
Aircraft performance

Airplane design

airspeed

Worldtech Asked on 16th June 2021 in Aerodynamics.
- 970 views
- 1 answers
- 0 votes
The reservoir of a supersonic wind-tunnel has a total temperature and total pressure of \(600\,K\) and \(11\,atm\). If the flow is isentropic through the nozzle of this wind tunnel, find the nozzle’s exit temperature and density if its exit pressure is \(1\,atm\).
The reservoir of a supersonic wind-tunnel has a total temperature and total pressure of \(600\,K\) and \(11\,atm\). If the flow …
Aircraft performance

Airplane design

Supersonic airplanes

Supersonic flow

techAir Asked on 15th April 2021 in Aerodynamics.
- 981 views
- 1 answers
- 0 votes
Find the enthalpy change, internal energy change and entropy change across a shock wave.
Find the enthalpy change, internal energy change and entropy change across a shock wave whose upstream air temperature and pressure …
Aircraft performance

Airplane design

airspeed

Shock waves

Supersonic flow

Worldtech Asked on 15th April 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of \(4.441\). The test section pressure measured by a pitot tube is \(1.5\, atm\).
Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of \(4.441\). …
Airplane design

airspeed

Supersonic flow

Kisan Kumar Asked on 26th March 2021 in Design.
- 1K views
- 1 answers
- 0 votes
A flow is passing over a \({20^ \circ }\) half-angle wedge having a upstream Mach number, pressure and temperature of \(2.8,\,1\,atm\,\) and \(310\,K\). Find the wave angle and 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 …
Airplane design

airspeed

Mach number

Shock waves

Kumar59 Asked on 11th March 2021 in Aerodynamics.
- 957 views
- 1 answers
- 0 votes
Find the pressure, temperature , Mach number, total pressure and total temperature behind the oblique shock wave.
An oblique shock wave is generated with a wave angle of \({30^ \circ }\) in a Mach \(4\) flow, at …
Airplane design

airspeed

Shock waves

Supersonic flow

Worldtech Asked on 11th March 2021 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Find the neutral point and static margin of an airplane if the location of the aerodynamic center is at \( 0.3\) chord length, the location of center of gravity is at \(0.38\) chord length, tail volume ratio is \(0.352\), tail lift slope is \(0.12\) per degree, lift slope of the wing body is \(0.085\) per degree and \(\frac{{\partial \varepsilon }}{{\partial \alpha }}\) from wind tunnel data is \(0.36\).
Find the neutral point and static margin of an airplane if the location of the aerodynamic center is at \( …
Aircraft performance

Airplane design

Worldtech Asked on 12th February 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes

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