uwochris
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- Joined
- Dec 21, 2001
- Posts
- 381
Hey guys,
It's my understanding that TAS is the equivalent airspeed corrected for density changes.
Here is a question from a work book that I can't quite figure out (or understand):
Pressure Alt: 33,000 ft.
IAS= 267 kts.
Instrument and Position error: +8 kts.
Compressibility error: - 13 kts.
Indicated OAT: -28 C.
Temperature Rise: 20 C.
a) 456 knots.
b) 477 knts.
c) 427 knts.
d) 433 knts.
To calc TAS, I used IAS+ instrument error- comp error (267 + 8 - 13= 262 knots). Then I used my E6B to calculate TAS using 33000 as my pressure altitude and -28C as the OAT. I get something close to 470 knots.
The correct answer, however, is a) 456 knots. What I do not understand is the "temperature rise" statement. What is this? How do I factor it into the TAS calculation.
Can anyone explain how to calculate the right answer?
Thanks,
Chris.
It's my understanding that TAS is the equivalent airspeed corrected for density changes.
Here is a question from a work book that I can't quite figure out (or understand):
Pressure Alt: 33,000 ft.
IAS= 267 kts.
Instrument and Position error: +8 kts.
Compressibility error: - 13 kts.
Indicated OAT: -28 C.
Temperature Rise: 20 C.
a) 456 knots.
b) 477 knts.
c) 427 knts.
d) 433 knts.
To calc TAS, I used IAS+ instrument error- comp error (267 + 8 - 13= 262 knots). Then I used my E6B to calculate TAS using 33000 as my pressure altitude and -28C as the OAT. I get something close to 470 knots.
The correct answer, however, is a) 456 knots. What I do not understand is the "temperature rise" statement. What is this? How do I factor it into the TAS calculation.
Can anyone explain how to calculate the right answer?
Thanks,
Chris.