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Search: Posts Made By: issaccph
Showing results 1 to 8 of 8
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Forum: Private Flying
28th Jul 2016, 13:08
Replies: 7
Views: 1,708
Posted By issaccph

Problem solved. Thanks again. I just found out...

Problem solved. Thanks again. I just found out what confusing me, the book doesn't explain it very well.

Anyway, thank you so much.
Forum: Private Flying
28th Jul 2016, 11:02
Replies: 7
Views: 1,708
Posted By issaccph

First of all, I would like to thank you for the...

First of all, I would like to thank you for the answers.

At the moment I am a private pilot and self-studying for the CPL knowledge from a set of books. To be honest, I do have basic theory in...
Forum: Private Flying
28th Jul 2016, 09:04
Replies: 7
Views: 1,708
Posted By issaccph

Is there any wingtip vortex (by induced drag) at low angle of attack?

Hi,

As I know, induced drag is an unavoidable product of lift and is directly related to the angle of attack. To produce lift, the static pressure on the upper surface of the wing is lower than...
Forum: Private Flying
26th Jul 2016, 07:26
Replies: 8
Views: 3,964
Posted By issaccph

Question on Flaps

Hi,

I am reading an aerodynamics book and feeling confused about two paragraphs which is about flaps.

"Think of the trailing-edge flaps at their early extension as lift flaps (when the lifting...
Forum: Private Flying
26th Jul 2016, 07:16
Replies: 8
Views: 4,028
Posted By issaccph

Thank you guys, I got it now.

Thank you guys, I got it now.
Forum: Tech Log
26th Jul 2016, 07:11
Replies: 5
Views: 10,599
Posted By issaccph

Thank you for all the efforts!

Thank you for all the efforts!
Forum: Tech Log
24th Jul 2016, 11:34
Replies: 5
Views: 10,599
Posted By issaccph

Effect of leading-edge flap on lift curve

Hi,

The graph below is captured from a aerodynamics book, and I got a question on the curve of L/E flaps.

http://i.imgur.com/I95VpDT.jpg

From what I have learnt, leading edge flaps (Droop or...
Forum: Private Flying
23rd Jul 2016, 12:00
Replies: 8
Views: 4,028
Posted By issaccph

Question about zero lift angle of attack

Hi,

For an average cambered wing like that found on a typical training aircraft, such as a Cessna 172, at about -4 angle of attack, the lift is zero and CL = 0.

But is it possible to achieve -4...
Showing results 1 to 8 of 8


 
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