uwochris
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- Joined
- Dec 21, 2001
- Posts
- 381
Hey guys,
I have some Qs that I would like some insight on. These come after I have been reading Kreshner's Advanced Pilot Manual.
1. I realize that if I am flying an a/c at 65 KIAS at sea level, and then I climb to 10,000 and maintain 65 KIAS, the only difference is the TAS. However, will the AOA of the 2 a/c be the exact same? I believe they should based on the lift equation, but I am not sure.
2. In the chapter on Glides, Kreshner mentions that weight has NO effect on the maximum distance that an aircraft can glide. ie. an a/c will glide the same distance at max gross weight than at a lighter weight, assuming you maintain the proper IAS (i.e. the correct AOA to fly at in a best glide situation). I just find it odd... I figure more weight=more drag, which should lower the glide ratio.
3. Assume 2 of the exact same make, model and configuration (including weight). Both are at 10,000 ft, and both lose their engine and pitch for the max glide distance AOA. Aircraft A is experiencing standard conditions, while a/c B is gliding in standard+ 20 degrees Celsius conditions. Will they glide the same distance? Kreshner seems to hint that you must use the same IAS for any given altitude or temperature (the glide IAS should only be changed with weight) and that your range will not be affected.
ie) a/c B will have a higher TAS, but it will also be burning more fuel, as more power is required to maintain a specific IAS in a warmer air mass. However, the ratio of nm/fuel burned will be approximately the same for both a/c.
Well, that's all *for now*
Thanks for any responses.
I have some Qs that I would like some insight on. These come after I have been reading Kreshner's Advanced Pilot Manual.
1. I realize that if I am flying an a/c at 65 KIAS at sea level, and then I climb to 10,000 and maintain 65 KIAS, the only difference is the TAS. However, will the AOA of the 2 a/c be the exact same? I believe they should based on the lift equation, but I am not sure.
2. In the chapter on Glides, Kreshner mentions that weight has NO effect on the maximum distance that an aircraft can glide. ie. an a/c will glide the same distance at max gross weight than at a lighter weight, assuming you maintain the proper IAS (i.e. the correct AOA to fly at in a best glide situation). I just find it odd... I figure more weight=more drag, which should lower the glide ratio.
3. Assume 2 of the exact same make, model and configuration (including weight). Both are at 10,000 ft, and both lose their engine and pitch for the max glide distance AOA. Aircraft A is experiencing standard conditions, while a/c B is gliding in standard+ 20 degrees Celsius conditions. Will they glide the same distance? Kreshner seems to hint that you must use the same IAS for any given altitude or temperature (the glide IAS should only be changed with weight) and that your range will not be affected.
ie) a/c B will have a higher TAS, but it will also be burning more fuel, as more power is required to maintain a specific IAS in a warmer air mass. However, the ratio of nm/fuel burned will be approximately the same for both a/c.
Well, that's all *for now*
Thanks for any responses.
