02-24-2022, 03:17 AM
This program computes the Static Air temperature of the air an aircraft is flying through. The formula:
SAT = TAT / (1+0.202 * R_c * Mach) is used
where SAT and TAT are kelvin
R_c is the probe recovery coefficient ~0.9-1.0 for most modern jets
Mach is the fraction of the local speed of sound.
In the program IAT is used in place of TAT since the recovery coefficient may not be 1 and thus the temperature is indicated not total.
The inputs and outputs for the program are in degrees Celsius.
SAT = TAT / (1+0.202 * R_c * Mach) is used
where SAT and TAT are kelvin
R_c is the probe recovery coefficient ~0.9-1.0 for most modern jets
Mach is the fraction of the local speed of sound.
In the program IAT is used in place of TAT since the recovery coefficient may not be 1 and thus the temperature is indicated not total.
The inputs and outputs for the program are in degrees Celsius.
Code:
LBL "SAT"
"TAT C?"
PROMPT
273.15
+
"MACH?"
PROMPT
X^2
"RECOVERY COEFF?"
PROMPT
*
0.202
*
1
+
/
273.15
-
FIX 1
"SAT: "
ARCL X
>"C"
AVIEW
END