
Supersonic flow has a Mach number
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The airfoil section of a wing is an NACA 2213 at the wing root, tapering to an NACA 2205 at …
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The temperature and pressure at the stagnation point of a high speed missile are \({934^ \circ }\) R and 7.8 atm, …
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Calculate the velocity at a point on the airfoil, where the pressure is \({\rm{0}}{\rm{.4 \times 1}}{{\rm{0}}^{\rm{5}}}{\rm{N/}}{{\rm{m}}^{\rm{2}}}\). The free stream velocity …
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In an inviscid, incompressible flow of air along a streamline, the air density is 0.002377 \({\rm{slug/f}}{{\rm{t}}^{\rm{3}}}\). At a point on …
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Lift per unit span of a spinning circular cylinder in a free stream with velocity of 50 m/s is 8 …
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Calculate locations on the surface of a cylinder where surface pressure equals to freestream pressure considering a nonlifting flow.
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Consider a nonlifting flow over a circular cylinder and derive an expression for the pressure coefficient at any arbitrary point \(\left( …
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Consider the non lifting flow over a circular cylinder of a given radius, where free stream velocity is \({V_\infty }\).If \({V_\infty …
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Calculate the peak coefficient of pressure for a lifting flow over a circular cylinder for which lifting coefficient is 70.
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