1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Consider the isentropic flow over an airfoil. The freestream conditions areT∞ = 245 K and p∞ = 4.35 × 104 N/m2. At a point on the airfoil, thepressure is 3.6 × 104 N/m2. Calculate the density at this point.

1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Consider the isentropic flow over an airfoil. The freestream conditions areT∞ = 245 K and p∞ = 4.35 × 104 N/m2. At a point on the airfoil, thepressure is 3.6 × 104 N/m2. Calculate the density at this point.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.68P

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Question

1 atm = 2116 lb/ft² = 1.01 × 10⁵ N/m².

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 3.6 × 10⁴ N/m². Calculate the density at this point.

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