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Title: Principles of Aerodynamics
Finance & Accounting
Pages 8 (2008 words)
Task # 1: 1. Area of the aircraft = A = 29 m2 Coefficient of Lift = CL = 0.67 Altitude = L = 29000 ft Velocity = v = 385 km/hr = 106.94 m/s Lift = FL =? Solution: Density at given altitude ‘A’ = air = 0.4671 kg/m3 (US Standard Atmosphere) Lift on an airfoil is given as FL = (?
air v2) A CD = (? (0.5) (v2)) (15) (0.054) = 1500 => v = 86.06 m/s 3. 4. 5. According to Bernard and Kermode, there are many different ways of defining the critical Mach number for an aircraft (308). The most common among these definitions is that which says that ‘a critical mach number refers to that Mach number of free stream at which Mach number of flow in the vicinity of the wing becomes unity’. This effect is shown in the following figure. Critical Mach Number (Anderson Introduction to flight 284) Other definitions may include the Mach number of free stream at which shock waves are produced or the Mach number at which air bubbles are generated or the Mach number at which a significant increase in drag coefficient is observed (Bernard and Kermode 308). As mentioned, the aircraft flying at critical Mach number experiences a high rise in drag. This happens because of deviation of flow field characteristics from ideal i.e. laminar flow around the airfoil. To improve the flow conditions or to avoid the unwanted flow conditions, different features are incorporated in an aircraft’s wings. The prominent among these are use of thinner wings and supercritical airfoils (Anderson Introduction 763). ...
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