4- A thin airfoil can be approximated as a flat plate. The airfoil is set at...
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4- A thin airfoil can be approximated as a flat plate. The airfoil is set at an angle of 10 to an airflow with a Mach number of 2, a temperature of -50 C, and a pressure of 50 kPa. Using linearized theory, find the pressures on the upper and lower surfaces of this wing. 5- An airfoil has a triangular cross-sectional shape. The lower surface of the airfoil is flat and the ratio of the maximum thickness to the chord is 0.1. The maximum thickness occurs at a distance of 0.3 times the chord downstream of the leading edge. If this airfoil is placed with its lower surface at an angle of attack of 2 to an airflow in which the Mach number is 3, use linearized theory to determine the distribution of the pressure coefficient over the surface of the airfoil. M = 3 c/3 0.1c 2c /3 4- A thin airfoil can be approximated as a flat plate. The airfoil is set at an angle of 10 to an airflow with a Mach number of 2, a temperature of -50 C, and a pressure of 50 kPa. Using linearized theory, find the pressures on the upper and lower surfaces of this wing. 5- An airfoil has a triangular cross-sectional shape. The lower surface of the airfoil is flat and the ratio of the maximum thickness to the chord is 0.1. The maximum thickness occurs at a distance of 0.3 times the chord downstream of the leading edge. If this airfoil is placed with its lower surface at an angle of attack of 2 to an airflow in which the Mach number is 3, use linearized theory to determine the distribution of the pressure coefficient over the surface of the airfoil. M = 3 c/3 0.1c 2c /3
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4 To find the pressures on the upper and lower surfaces of a thin airfoil set at an angle to an airflow using linearized theory we can use the Prandtl... View the full answer
Related Book For
Fundamentals Of Momentum Heat And Mass Transfer
ISBN: 9781118947463
6th Edition
Authors: James Welty, Gregory L. Rorrer, David G. Foster
Posted Date:
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