Principles of Aerodynamics Coursework Example | Topics and Well Written Essays - 2000 words

Principles of Aerodynamics - Coursework Example2 Coefficient of Drag = CD = 0.054 Area = S = 15 m2 Thrust = T= 1500 N Density= A = 0.5 kg/m3 For a steady and level flight, shack force is equal to the thrust produced by engines, D = T = 1500 N D = (? A V?2) S CD = (? (0.5) (V?2)) (15) (0.054) = 1500 = V? = 86.06 m/s = 8.6 E +1 m/s Question No. 3 Question No. 4 The sketches shown below decorate the trend of variation in CL, CD, and L/D ratios with increasing angle of attack. Question No. 5 Critical Mach tote up corresponds to that value of Mach number for free stream endure for which a localized mach number of 1 is obtained at any point around the airfoil. When this condition arises, a shock wave is created at the point where the flow reaches the sonic speed. As the speed increases, regions of very low pressure are created. This causes the flow to separate from the airfoil thereby substantially increasing the drag forces on it. The figure illustrates this phenomenon. Some of the a ll important(predicate) design features incorporated in the aircrafts in order to contain the effects of this situation are apply thin airfoil and / or super critical airfoil (Anderson Introduction 763). Making an airfoil depressed increases the value of Critical Mach Number and hence the airplane can fly at very towering speeds without a significant increase in drag forces on it. ... Their unique design limits the rise of drag forces even after the critical mach number is reached. Such airfoils have successfully been utilized in adroitness aircraft program run by NASA Dryden Flight Research Center (Cury). Question No. 6 In the above illustration, the triangle represents the fuselage of an aircraft as seen from front. is the angle of bank for the turn. LV = L romaine LH = L sin The centripetal force required by the aircraft to take the turn is provided by horizontal helping of lift force given by LH, equating the two L sin = (a) the component LV balances the weight of th e aircraft, hence = L cos = mg From the above equation, L = mg / cos putt values in (a) and simplifying g tan = putting values for = 15o and r = 1500 m gives v = 62.79 m/s Load Factor = L/W = L/L cos = 1/ cos = 1/cos 15o = 1.035 Question No. 7 Following are the secure surfaces used to control the motion of an aircraft along different axes (1) The longitudinal axis Ailerons (2) The Vertical or Normal Axis Rudder (3) The squint-eyed Axis Elevator The figure shows the above mentioned control surfaces and the functions they perform. All the control surfaces work on the normal of creating drag for the incoming wind thereby changing the direction of the wind. Due to this change in velocity, a momentum change occurs which causes a force to act on the control surface and the desired nominal head of the aircraft is achieved this way. The ailerons tilt the aircraft around the longitudinal axis. They are always installed in pairs. The opposite motion of the two ailerons creates a co uple which acts about the longitudinal axis to cause the desired motion. Rudder rotates the