• Question Tag: incompressible flow
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• ## 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 …

Asked on 1st September 2021 in
• 232 views

A pitot tube of an airplane which is flying at an standard sea level measures a pressure of $$1.09 \times … Asked on 16th June 2021 in • 215 views • 1 answers • 0 votes • ## Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has an inlet -to-throat area ratio of \(10$$.

Find the velocity of air in the test section of a low speed open circuit subsonic wind tunnel which has …

Asked on 15th June 2021 in
• 203 views
• ## Find the velocity of an airplane flying at a standard sea level, if the static pressure at the throat of venturi is $$100 000 N/m^{2}$$.

A venturi is attached on a side of an airplane fuselage, has an throat to inlet area ratio of $$0.8$$.  …

Asked on 15th June 2021 in
• 202 views
• ## Bernoulli’s principle and equation

What is Bernoulli’s theorem ?

Asked on 8th December 2020 in
• 355 views

Consider an incompressible two-dimensional viscous flow over a curved surface .Let the pressure distribution on the surface be $$p(s)=2+sin\left ( … Asked on 30th December 2019 in • 518 views • 1 answers • 0 votes • ## Calculate the lift and induced drag coefficients for the 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 …

Asked on 12th November 2019 in
• 1K views
• ## 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}} …

Asked on 11th November 2019 in
• 2K views
• ## 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 …

Asked on 10th November 2019 in
• 652 views
Consider a thin, symmetric airfoil at $$1.5^{\circ}$$ angle of attack. From the results of thin airfoil theory, calculate the lift …