View Full Version : Mach TAS and SAT
fernando
1st Feb 2005, 21:08
HI
As far as I can remember for a given Mach number and a Static air temperature there is a unique True air speed.
How are they related?
I will need and equation which should look like this:
TAS=M*constant*SAT
I can also handle square roots and fractions.
Many thanks
john_tullamarine
1st Feb 2005, 22:14
If you want to strain the grey matter a bit, refer to any standard undergrad aerodynamics text .. in essence, the story is
M = TAS/local speed of sound
where local speed of sound, a
a/a0 = SQRT (T/T0)
where subscript 0 indicates standard sea level values and T is absolute (Kelvin or Rankine),
eg a0 = 661.48 kt and T0 = 288.15 K = 15 C
Rearranging for TAS
= M * a
= M * a0/SQRT(T0) * SQRT(T)
Substitute for whatever system of units is your cup of tea .. add a few unit conversion factors to taste and you end up with the sort of equation you are looking for .. something along the lines of
For
TAS kt
OAT C
= M * 661.48 / SQRT(288.15) * SQRT(273.15 + C)
= 38.97 * M * SQRT(273.15 + C)
(assuming I haven't made any numeric errors along the way .. )
fernando
2nd Feb 2005, 20:31
I got it. thank you.
blackmail
4th Feb 2005, 09:15
hello every one
tas= 661.M.sqrt theta with theta=T\Ts T=(273+sat°c )K Kelvin & Ts=288K(273+15°c)
to find this formula:
tas=M.a & a square=k.R.T k=1.4 for dry air =cte
R(universal gas cte)=287joules\kg & K
T=temperature in kelvin
now take above formula & multiply & divide at the same time by a0=speed of sound at sea level=661kts.
so: tas=ao.M.squareroot of k.R.T\squareroot of k.R.Ts
a0square being of course=k.R.Ts
theta=k.R.T\k.R.Ts=T\Ts
so finally: tas=661.M.sqrt theta
equally eas=661.M.sqrt delta with delta=p\po p=atm pressure in Hpa & po=1013.25Hpa
delta=sigma x theta ; sigma=rho(density in kg\m3)\rhozero
rhozero=1.225kg\m3
to find above formulas think of mr boyle's gas laws: p=rho.R.T & po=rhozero.R.Ts divide both formulas & find: p\po=rho\rhozero x T\Ts
thus: delta=sigma x theta
conclusion: tas=function of mach & temperature whereas ias & eas are function of mach & pressure
so we see it every day in climb:
first climb at cte eas, mach increases & theta decreases
then at crossover altitude climb at cte mach & eas & delta now decreases.
stop here before my headache starts again
I can confirm
LSS = 38.95 x SQR (temp Kelvin)
or
LSS = 38.95 x SQR (temp C + 273)
LSS = Local speed of sound (KTAS). Multiply by desired Mach number to get the appropriate TAS.
I can recommend "Air Data Conversion" programme, should be available on http://www.avionic-cbt.co.uk/adc/adcsetup.exe but it does not work right now? It is a 30-day trial version.
Edited for an "oops" ...
Old Smokey
5th Feb 2005, 05:05
LGB,
I think you'll get slightly better results if you use a Constant of 38.97, and use +273.15 for your conversion to Absolute Temperature.
Oh Gawd ! I'm becoming too pedantic.
Regards,
Old Smokey
GearDoor
7th Feb 2005, 00:19
Wow, I'm really impressed with the scientific knowledge of some of the members to this website. I knew the answer to the initial question was something like 39 * sqrt(temp (K)), but I had no idea some of you people could readily derive the equation. I have an engineering degree, so I could follow the logic of the responses, but I didn't know the original form of the equation. Kudos!
john_tullamarine
7th Feb 2005, 02:15
.. stock standard undergrad aero eng textbook stuff ..