Airfoil analysis

[JoeSpencer1]

I have created files for more different real airfoils for a real comparison instead of just doubling the y vectors.

[Cardoza2]

Comments on your glossary/dictionary:

• The tip and tail of an airfoil have names, it's the leading edge and trailing edge.
• The lift curve slope isn't typically used to see the total change in lift, because typically you have multiple airfoils along a wing. The lift curve slope only applies for one section (unless of course you do in fact have the same airfoil along the entire wing).
• Stall can also occur at negative angles of attack.

[Cardoza2]

Comments on write up:

• I wouldn't say that the lift and drag are controlled by equation one. Rather those equations are from the non-dimensionalization of lift and drag, so you can get lift and drag from the coefficients.
• Equations doesn't need to be capitalized unless it is at the beginning of a sentence.
• In the beginning you mention changing chord and camber, but not thickness or Reynolds number, then that's what you do... and you don't end up changing chord. So... I'd be consistent.
• just before table 1 you have an incomplete sentence.
• It would be interesting to know why the drag isn't the lowest at alpha=0.
• Does increasing alpha ALWAYS increase lift? What about in the stalled region?
• Second to last paragraph on page 3, I'm not sure what you meant about plotting on different planes.
• Bottom of page 3, which graphs shown in figures 1 and 2?
• When you say critical angle of attack, do you mean zero-lift angle of attack? There are multiple "critical" angles of attack. Some people define the any important angle of attack as a critical angle of attack. Other's define stall as the critical angle of attack.
• You did such a good job talking about how the Reynolds numb and Camber affect the polars, but then you skimp on the thickness. Did you not have much to say on the thickness?
• There seems to be some repetition of comments and thoughts throughout, which isn't entirely bad, but it starts to come off as scattered.
• I think it'd be good if you had a little more on the lift curve slope. Feel free to ask me a little more on this.
• Wow, that was pretty good. Good job.

[JoeSpencer1]

I am merging this branch back into my main 497-R branch now.