Aircraft performance Archives - Page 3 of 8

Question Tag: Aircraft performance

All Questions

Filter by

Questions Per Page:

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.
- 949 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
What are jet engine and scramjet engine ?
What are jet engine and scramjet engine ?
Aircraft performance

Supersonic airplanes

turbojet

techAir Asked on 7th September 2021 in Propulsion.
- 1K 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
An airplane is cruising at \(50\,m/s\) at standard sea level in straight and level flight. The airplane has a wing area of \(15\,m^2\) and a wing span of \(10\,m\), and has the maximum gross weight of \(1000\,kg\). The airfoil of the wing has lift slope of \(0.102\) per degree and angle of attack at zero lift of \(-2.5^{\circ}\). Considering, \(\tau = 0.1\), find the angle of attack for the wing. Also, find the induced drag for the airplane, if span efficiency factor is \(0.6\).
An airplane is cruising at \(50\,m/s\) at standard sea level in straight and level flight. The airplane has a wing …
Aircraft performance

airfoil

Induced drag

techAir Asked on 12th August 2021 in Aeronautics.
- 912 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.
- 954 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.
- 962 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 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
Consider wing-body combination of an airplane. Find the coefficient of lift of this wing body if the coefficient of moment about the center of gravity and the coefficient of moment about aerodynamic center is \(0.006\) and \(-0.015\). Aerodynamic center is forward of the center of gravity at \(0.035\) chord length.
Consider wing-body combination of an airplane. Find the coefficient of lift of this wing body if the coefficient of moment …
Aircraft performance

Airplane design

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

Tags

LATEST QUESTIONS

Tags