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Consider the isentropic flow over an airfoil. The freestream conditions are T∞ = 245 K and p∞ = 4.35 × 104 N/m². At a point on the airfoil, the pressure is 3.800 × 104 N/m². Calculate the density at this point. (Round the final answer to three decimal places.) The density at the given point is kg/m³

Consider the isentropic flow over an airfoil. The freestream conditions are T∞ = 245 K and p∞ = 4.35 × 104 N/m². At a point on the airfoil, the pressure is 3.800 × 104 N/m². Calculate the density at this point. (Round the final answer to three decimal places.) The density at the given point is kg/m³

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Consider the isentropic flow over an airfoil. The freestream conditions are T∞ = 245 K and p∞ = 4.35 × 104 N/m². At a point on the airfoil, the pressure is 3.800 × 104 N/m². Calculate the density at this point. (Round the final answer to three decimal places.) The density at the given point is kg/m³
Transcribed Image Text:Consider the isentropic flow over an airfoil. The freestream conditions are T∞ = 245 K and p∞ = 4.35 × 104 N/m². At a point on the airfoil, the pressure is 3.800 × 104 N/m². Calculate the density at this point. (Round the final answer to three decimal places.) The density at the given point is kg/m³
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