Unformatted text preview: Due Thursday, December 9th by noon Reading Assignment: Chapter 6 and Section 17.6 of your textbook. 1. A sharp cone with a halfcone angle of θ c = 15 o is tested in a hypersonic wind tunnel at a Mach number of 10.6 at zero degrees angle of attack. If the total pressure and the total temperature at the stagnation chamber of the wind tunnel are 1200 psi and 2000 o R respectively and assuming the temperature of the cone surface (wall € temperature) is 560 o R : a. Using the reference temperature method, estimate the shear stress and the heat transfer to the wall at a location 14.3 inches away from the apex measured along the cone surface assuming laminar flow. € b. Using the reference temperature method, estimate the shear stress and the heat transfer to the wall at a location 14.3 inches away from the apex measured along the cone surface assuming turbulent flow. 2. Consider the spherically blunted biconic nose geometry of a hypersonic ICBM shown in Question 1 of homework 5. Assuming the same freestream conditions given in that question (freestream Mach number of M∞ = 18 at an altitude of 15 km and zero degrees angle of attack) and a wall temperature of Tw = 2000 K , a. Calculate the stagnationpoint heat transfer for the given nose cone geometry using calorically perfect gas assumption € b. Calculate the stagnationpoint heat transfer for the given nose cone geometry using air in thermochemical equilibrium€ assumption (Assume that the term including the Le number is approximately equal to 1.0, i.e., neglect the heat transfer due to diffusion by assuming hD = 0.0) . AE369 Homework 6, Fall 2010 € € ...
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 Fall '10
 SerhatHosder
 Fluid Dynamics, Aerodynamics, Heat Transfer, reference temperature method, cone surface, nose cone geometry

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