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What is a induced drag ?
What is a induced drag ?
Airplane design

drag

drag force

lift and drag

Worldtech Asked on 17th June 2020 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Poll Concorde airplane is
Concorde airplane is
Aircraft performance

Airplane design

Kumar59 Asked on 16th June 2020 in Aeronautics.
- 576 views
- 4 answers
- 0 votes
Define absolute ceiling and service ceiling of an aircraft.
Define absolute ceiling and service ceiling of an aircraft.
Airplane design

flight mechanics

Kisan Kumar Asked on 31st December 2019 in Flight mechanics.
- 2K views
- 1 answers
- 0 votes
The measured lift slope for the NACA \(23012\) airfoil is \(0.1080\; degree^{−1}\), and \(α_{L}=0 = −1.3^{\circ}\). Consider a finite wing using this airfoil, with AR = \(8\) and taper ratio = \(0.8\). Assume that \(δ = τ\) . Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack = \(7^{\circ}\).
The measured lift slope for the NACA \(23012\) airfoil is \(0.1080\; degree^{−1}\), and \(α_{L}=0 = −1.3^{\circ}\). Consider a finite wing …
airfoil

Airplane design

incompressible flow

Worldtech Asked on 12th November 2019 in Flight mechanics.
- 3K views
- 1 answers
- 0 votes
Using thin airfoil theory, calculate \( (a) α_{ L=0}\) (b) \(cl\) when \(α = 3^{\circ} \).
The NACA 4412 airfoil has a mean camber line given by\[\frac{z}{c} = \left\{ {\begin{array}{*{20}{c}} {0.25\left[ {0.8\frac{x}{c} – {{\left( {\frac{x}{c}} \right)}^2}} …
airfoil

Airplane design

incompressible flow

Worldtech Asked on 11th November 2019 in Aerodynamics.
- 4K views
- 1 answers
- 0 votes
Consider a thin, symmetric airfoil at \(1.5^{\circ}\) angle of attack. From the results of thin airfoil theory, calculate the lift coefficient and the moment coefficient about the leading edge.
Consider a thin, symmetric airfoil at \(1.5^{\circ}\) angle of attack. From the results of thin airfoil theory, calculate the lift …
airfoil

Airplane design

incompressible flow

techAir Asked on 9th November 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Starting with the definition of circulation, derive Kelvin’s circulation theorem.
Starting with the definition of circulation, derive Kelvin’s circulation theorem.
airfoil

Airplane design

incompressible flow

Worldtech Asked on 9th November 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Consider an NACA \(2412\) airfoil with a \(2\;m\) chord in an airstream with a velocity of \(50\; m/s\) at standard sea level conditions. If the lift per unit span is \(1353\; N\), what is the angle of attack?
Consider an NACA \(2412\) airfoil with a \(2\;m\) chord in an airstream with a velocity of \(50\; m/s\) at standard …
Aircraft performance

airfoil

Airplane design

incompressible flow

Worldtech Asked on 8th November 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Consider the data for the NACA \(2412\) airfoil. Calculate the lift and moment about the quarter chord (per unit span) for this airfoil when the angle of attack is \(4^{\circ}\) and the freestream is at standard sea level conditions with a velocity of \(50 ft/s\). The chord of the airfoil is \(2 ft\).
Consider the data for the NACA \(2412\) airfoil. Calculate the lift and moment about the quarter chord (per unit span) …
Aircraft performance

airfoil

Airplane design

incompressible flow

Worldtech Asked on 8th November 2019 in Aerodynamics.
- 4K views
- 1 answers
- 0 votes
Poll When is the critical Mach number of an airfoil attained ?
The critical Mach number of an airfoil is attained when
airfoil

Airplane design

GATE

Kisan Kumar Asked on 1st October 2019 in Design.
- 725 views
- 1 answers
- 0 votes

Poll Concorde airplane is

Poll When is the critical Mach number of an airfoil attained ?

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