The stagnation temperature I recall is roughly given by the following:

Ts/T1 = (1 + (M^2)/5)

"Mike Rapoport" wrote in message
link.net...

I have flight manuals that give a correction for airspeed and altitude and
the numbers are much higher than 3C even though the speeds are below M0.5.
In the MU-2, the temp sensor is in the tail section where the cross
section of the fusilage is actually decreasing..

I think the problem is only with the numbers that got plugged in. At M =
0.5, you get
Ts/T1 = 1.05. In other words a 5% temp rise. 5% of about 273 K is about 13
K,
i.e. 13 degC.

Is there both a compression and a friction heating of surfaces due to
airflow?

It's the same phenomenon. The "friction" occurs because the air is brought
to stagnation in the boundary layer.

Julian Scarfe