1.

A thin airfoil is defined as NACA 0009 is at ɑ = 5°. What is the value of lift curve slope?(a) 2ᴨ per rad(b) 2ᴨ per degree(c) 4 per degree(d) 0.4 per degreeThis question was posed to me during an interview for a job.My query is from Airfoil Selection-2 topic in division Airfoil and Geometry Selection of Aircraft Design

Answer»

Right answer is (a) 2ᴨ per rad

Best explanation: Given, NACA0009 airfoil,

AOA ɑ = 5°

As mentioned the airfoil is thin. HENCE, thin airfoil THEORY can be used.

According to thin airfoil theory, for thin airfoil,

LIFT CURVE slope = 2π 1/rad = 0.11 1/degree.



Discussion

No Comment Found

Related InterviewSolutions