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Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach \(2.5\) freestream flow …
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Why is critical Mach number of a sphere higher than a cylinder ?
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Velocity potential of a subsonic compressible flow is \[\phi(x,y) = V_{\infty}x + \frac{5}{\sqrt{1 – M_{\infty}^{2}}}e^{-2\pi\sqrt{1-M_{\infty}^{2}}y}sin2\pi x\] Freestream velocity, pressure and …
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An airfoil is in airflow with \(0.52\) free stream Mach number. Local Mach number at a given point is \(0.82\). …
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What are stagnation pressure and stagnation temperature ?
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A circular cylinder and a sphere are in a free stream flow with their axis perpendicular to the flow. At …
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A NACA 4421 airfoil having a chord length of \(2\,m\) is flying at an velocity of \(70\,m/s\) at an altitude …
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An airfoil has a lift coefficient and moment coefficient of \(-0.35\) and \(-0.050\) about quarter-chord at \(-6^{\circ}\) angle of attack. …
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A positively cambered airfoil has a zero-lift angle of \(-3.5^{\circ}\). The lift slope for this airfoil is \(0.12\) per degree. …
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Find the circulation around a spinning circular cylinder in free stream flow of velocity \(40\,m/s\) at a standard sea level …
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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.
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Why is critical Mach number of a sphere higher than a cylinder ?
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Find the velocity, pressure and temperature at, \((0.07\,m, 0.07\,m)\).
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Find the pressure coefficient at this point.
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How urban air mobility work?
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