{[ promptMessage ]}

Bookmark it

{[ promptMessage ]}

quiz-solution10

# quiz-solution10 - 650:460 Aerodynamics Quiz No 10 Solution...

This preview shows pages 1–4. Sign up to view the full content.

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: 650:460 Aerodynamics Quiz No. 10 - Solution Prof. Doyle Knight Tel: 732 445 4464, Email: [email protected] Oﬃce hours: Tues and Thur, 4:30 pm - 6:00 pm and by appointment Fall 2009 1 Quiz No. 10 Consider the two dimensional airfoil shown in the ﬁgure. The freestream Mach number M∞ = 3 and the angle of attack α = 2.5◦ . The angle δ = 5◦ . Calculate the section lift coeﬃcient cl and drag coeﬃcient cd . 2 Quiz No. 10 Solution The lift coeﬃcient is cl = The drag coeﬃcient is cd = Now 2 σu 4α 2 M∞ − 1 = 0.0617 4α2 2 M∞ −1 + 2 2 M∞ −1 2 σu + σl2 1 = c c o dz dx 2 dx = 1 c c (tan δ )2 dx = tan2 δ o 3 Quiz No. 10 Also, σl2 = 0 Note that the mean chord line is the straight line connecting the leading and trailing edges. This is the same as the bottom surface of the airfoil and consequently σl2 = 0. Thus cd = 8.105 · 10−3 4 ...
View Full Document

{[ snackBarMessage ]}

### Page1 / 4

quiz-solution10 - 650:460 Aerodynamics Quiz No 10 Solution...

This preview shows document pages 1 - 4. Sign up to view the full document.

View Full Document
Ask a homework question - tutors are online