techAir's Profile

454
Points

Questions
69

78

• ## What are jet engine and scramjet engine ?

What are jet engine and scramjet engine ?

Asked on 7th September 2021 in
• 59 views
• ## 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 …

Asked on 12th August 2021 in
• 90 views
• ## Find the location of the aerodynamic center.

An airfoil has a lift coefficient and moment coefficient of $$-0.35$$ and $$-0.050$$ about quarter-chord at $$-6^{\circ}$$ angle of attack. …

Asked on 22nd July 2021 in
• 121 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 • 110 views • 1 answers • 0 votes • ## Find the angular velocity about the \(z$$-axis, acceleration and the vorticity at point $$(2,3,5)$$ at $$t = 3$$ seconds.

A velocity field is given by $$V= 5xyi+8txzj+xzk$$. Find the angular velocity about the$$z$$-axis, acceleration and the vorticity at …

Asked on 5th May 2021 in
• 253 views
• ## Find the circulation around a closed contour which is defined by $$x = 1, y = 0, y = 1$$ and $$x = 0$$.

A velocity field is given by $$u=x^{2} + y$$ and $$v= x^{3} + 2y$$. Find the circulation around a closed …

Asked on 15th April 2021 in
• 172 views
• ## 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 …

Asked on 15th April 2021 in
• 165 views
• ## Find the combustion chamber pressure of a rocket engine.

Find the combustion chamber pressure of a rocket engine using hydrogen and oxygen as propellants, whose mass flow in combustion …

Asked on 26th March 2021 in
• 129 views
• ## Find the Mach number, pressure and temperature behind the reflected shock wave and angle made by the reflected shock wave with the upper wall.

An oblique shock wave is generated at a compression corner having a deflection angle of $$20^{^{\circ}}$$. The oblique shock wave …

Asked on 26th March 2021 in
• 174 views
• ## Find the upstream Mach number if there is a entropy increase across the normal shock wave of $$220\,J/\left( {kg.K} \right)$$.
Find the upstream Mach number if there is an entropy increase across the normal shock wave of $$220\,J/\left( {kg.K} \right)$$.