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question an airplane weighing 100 kn has a span of 195 m and a wing loading of 1925 k nm-2 the wings are rather sharply
question show that the downwash angle at the center span of the tailplane is given to a good approximation byepsilon
question an airplane weighing 100 kn is 244 m in span its tailplane which has a symmetrical section and is located 152
question three airplanes of the same type having elliptical wings with an aspect ratio of 6 fly in vee formation at 67
question 1 the spanwise distribution of circulation along an untwisted rectangular wing of aspect ratio 5 can be
question a straight wing is elliptic and untwisted and is installed symmetrically in a wind tunnel with its centerline
question determine how downstream mach number varies with upstream mach number for a fixed turning angle specifically
question consider a mach 2 flow that encounters a 15-degree compression corner and then a 15-degree expansion corner
question a converging-diverging nozzle is supplied with air at a total pressure of 250 psi the area of the throat is 01
question use thin-airfoil theory to select a naca four-digit wing section with a coefficient of lift at zero incidence
question a thin two-dimensional flat-plate airfoil is fitted with a trailing-edge flap of chord 100e of the airfoil
question a thin airfoil has a circular-arc camber line with a maximum camber of 0025 chord determine the theoretical
question the camber line of a circular-arc airfoil is given byderive an expression for the load distribution pressure
question a flat-plate airfoil is aligned along the x-axis with the origin at the leading edge and trailing edge at x c
question use thin-airfoil theory to select a naca four-digit wing section with a coef- ficient of lift at zero
question 1 an airplane weighing 736 kn has elliptic wings 1523 m in span for a speed of 90 ms-1 in straight and level
question obtain an expression for the downward induced velocity behind a wing of span 2s at a point of distance y from
question for a wing with modified elliptic loading such that at distance y from the center of the span the circulation
question the velocity components of a two-dimensional inviscid incompressible flow are given byfind the stream function
question define the terms velocity potential circulation and vorticity as used in twodimensional fluid mechanics and
question write the velocity potential for the two-dimensional flow about a circular cylinder with a circulation gamma
question a line vortex of strength gamma is mechanically fixed at the point l 0 in space described by a cartesian
question define the stream function the irrotational flow and the velocity potential for two-dimensional motion of an
question state the stream function and velocity potential for each of the motions induced by a source vortex and
question a rectangular untwisted wing of aspect ratio 3 has an airfoil section for which the lift-curve slope is 6 in