Questions About Stagnation Temperatures

[Jetpipe.]

Since equations link airspeeds to eachother

• EAS=TAS sqrt(ρ/ρ0)

where ρ= actual density , and ρ0= standard density at sea level 1.225 kg/m^3

• M = TAS/sqrt(γ R T)

where γ= the adiabatic indeex (1.4) , R= the specific gas constant (286.9 J/kg K) , and T= Static Air Temperature in Kelvin

The Ram Rise equations are linked in the same way. We choose for which airspeed we want the TAT-SAT equation to be solved for, TAS, Mach or EAS.

• TAT - SAT = TAS^2 / 2Cp

• TAT - SAT = 0.5 M^2 (γ-1) SAT

or for others more convinient TAT/SAT = 1 + [(γ-1)/2] M^2

• TAT - SAT = (ρ0/ρ) EAS^2 / 2Cp

Jetpipe.