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Calculate the lift, drag and moment coefficient about quarter chord per unit span of an airfoil which is at an angle of attack of \({7\, ^ \circ }\) with a flow velocity of \(40\, m/s\) at standard sea level conditions. The airfoil has a chord length of \(1\, m\).
Calculate the lift, drag and moment coefficient about quarter chord per unit span of an airfoil which is at an …
Aircraft performance

airfoil

Airplane design

airspeed

lift and drag

Kumar59 Asked on 4th January 2021 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
What is the difference between symmetrical and asymmetrical /cambered airfoil?
What is the difference between symmetrical and asymmetrical /cambered airfoil?
Aircraft performance

airfoil

Airplane design

airspeed

lift

techAir Asked on 17th December 2020 in Design.
- 5K views
- 1 answers
- 0 votes
Airfoil Terminology and NACA Series of airfoil Nomenclature.
Define airfoil terminology and NACA series of airfoil nomenclature.
Aircraft performance

airfoil

Airplane design

airspeed

lift force

Worldtech Asked on 10th December 2020 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
What is flaps and what are they used for?
What is flaps and what are they used for?
Aircraft performance

airfoil

Airplane design

airspeed

lift and drag

techAir Asked on 2nd December 2020 in Flight mechanics.
- 1K views
- 1 answers
- 0 votes
Poll Stall in an aircraft occurs when
Stall in an aircraft occurs when there is a flow separation and reduction in the lift coefficient of the airfoil. …
Aircraft performance

airfoil

Airplane design

Kisan Kumar Asked on 6th July 2020 in Flight mechanics.
- 636 views
- 2 answers
- 0 votes
What is critical Mach number?
What is critical Mach number?
Aircraft performance

airfoil

Airplane design

Mach number

techAir Asked on 25th June 2020 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
For the NACA \(2412\) airfoil, the lift coefficient and moment coefficient about the quarter-chord at \(−6 ^{\circ}\) angle of attack are \(−0.39\) and \(−0.045\),respectively. At \(4^{\circ}\) angle of attack, these coefficients are \(0.65\) and \(−0.037\),respectively. Calculate the location of the aerodynamic center.
For the NACA \(2412\) airfoil, the lift coefficient and moment coefficient about the quarter-chord at \(−6 ^{\circ}\) angle of attack …
aerodynamic center

airfoil

incompressible flow

Worldtech Asked on 10th November 2019 in Aerodynamics.
- 2K 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

Poll Stall in an aircraft occurs when

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