Use scale analysis to find an expression for 8/x and Nu for flow over a flat plate with a thin thermal boundary Layer. Find the expression 8/x = 4.92 Re** Consider the following NACA airfoils: 2412, 23012, 23021 a. For each of these airfoils, find the L/D ratio for angle of attack of 0, 4, 8 and 12 b. For each airfoil find the angle of maximum L/D and find the stall angle c. Find which airfoil will provide the maximum lift for any given geometry and flow conditions

A two-dimensional airfoil (object 1) is subject to air flow of upstream velocity 28 m/s. The upstream air pressure and temperature are 0.4 atm and 280 K, respectively. The characteristic length of object 1 is 25 mm and its surface temperature is uniform at 320 K. Now, a geometrically similar airfoil (object 2) with different characteristic length 167 mm is placed in water flow. The upstream water temperature is 300 K and the surface temperature of object 2 is uniformly at 310 K. What is the upstream water velocity in m/s for object 2 such that the boundary layer analogy exists between the two cases? Note that liquid water properties can be approximated as those for a saturated liquid at the same temperature. Object 1 Tsl Air Tool V₁ Li Water Too2 V₂ Object 2 L₂ T₁2

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Air at 15°C flows at 10 m/s over a flat plate of length 3 m. Using one-seventh power law of the turbulent flow, what is the ratio of local skin friction coefficient for the turbulent and laminar flow cases? (The kinematic viscosity of air is 1.470 × 10−5 m2/s.) (a) 4.25 (b) 5.72 (c) 6.31 (d ) 7.29 (e) 8.54