Power curves
 

Can someone give me a detailed and accurate explanation of the connection between the thrust curves vs drag and the power required/power available curves. I specifically want to understand what happens to the following when weight is reduced during a climb:
Rate of climb
Angle of climb
IAS and TAS.
All this is assuming non-turbocharged piston engined aircraft
Thx



[This message has been edited by shenebix (edited 10 March 2001).]

shenebix,

That would take a lot of space to adequately explain. I suggest a book titled, "Aerodynamics for Naval Aviators" by H. H. Hurt. I don't know you're background, but this book explains things very well without all the mathematical derivation. Hope this helps. Take care.

Amin

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Sentry IP

Thx for your suggestion. My background is primarily flight instruction would you believe but I have always had this gap with an explanation that satisfies me. Will seek out that book
Cheers

shenebix,

The questions you have asked required a degree of explaination to answer. If you are genuinely interested in the subject, I would suggest looking at something like "Aircraft Flight" by Barnard and Philpott. Its a good elementary flight mechanics book, but covers a wide range of subjects in good detail. You should be able to get it from any big bookstore.

Hope this helps,

Cuban_8

Cuban_8
Thanx for the repy and another book suggestion
Shenebix

There is no easy way to explain it without the use of diagrams.

In addition to "Aerodynamics for Naval Aviators" you might want to check out:
"Mechanics of Flight" by A C Kermode.

I found both useful during my time as an Instructor.

If you don't change the airspeed, CG/trim when you reduce weight, the problem reduces to a simple one as drag and power available are constant.

I.e there is the same amount of surplus power available to climb so the rate of climb is inversely proportional to the weight (work rate or power = mass * g * vertical speed) and the cosine of the climb gradient is proportional to the rate of climb at a given TAS.