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question a thin plate of length 50 cm is held in uniform water flow such that its length is parallel to the flow
question use the shock-expansion method to solve for the lift and drag coefficients of the cross-section of the saturn
question examine the flow over the supersonic airfoil illustrated in fig using shock-expansion theory assume that the
question consider a two-dimensional flat plate inclined at a positive angle of attack of 10 degrees in a supersonic air
question a four-bladed airscrew is required to propel an aircraft at 125 ms-1 at sea level with a rotational speed of
question a three-bladed airscrew is driven at 1560 rpm at a flight speed of 110 m s-1 at sea level at 125-m radius the
question a closed-return wind tunnel with a large contraction ratio has air at standard conditions of temperature and
questionnbspon the basis of bernoullis equation discuss the assumption that the compressibility of air may be neglected
question a convergent-divergent duct has a maximum diameter of 150 mm and a pitot- static tube is placed in its throat
question if we call your answer to exercise w1 xz and add in a uniform flow field of velocity vmacrinfin ui where i
question given a horseshoe vortex of strength 0 find the induced velocity field at all points in xz space where y 0
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