# mach number and temprature

Thread Starter

Join Date: Dec 2018

Location: islamabad

Posts: 1

**mach number and temprature**

hello every one. I have a question. If mach number is achieved at 500 TAS at 10 degrees Celsius, then at 50 degree Celsius how much TAS is required to achieve a mach number. kindly proof answer with the help of mathematical relationship. i will be very thank full to you guys, regards

Join Date: Feb 2000

Location: UK

Posts: 13,484

The local speed of sound is the square root of gamma * R * T

gamma is the diatomic gas constant, 1.4

R is the gas constant for dry air - 287 kJ/kg.K

T is the temperature in Kelvin.

50 degrees C is 323.15 Kelvin.

SQRT (1.4 x 287 x 323.15) = 360 m/s.

If you prefer knots, divide by 0.5144

And you get c = 700 knots.

If you have a local True Airspeed, divide that by c, and you get the Mach number. So, say you are flying at 500 knots TAS, in an air mass at 50deg.C, then your Mach number is 500/700 = 0.714.

Don't forget that if you are working in IAS or EAS, you need to make further conversions - and in particular at non ISA temperatures, even at sea level, you need to correct the EAS/TAS relationship for density altitude. Ideal gas laws are your friend again here.

So relative density = (pressure / standard sea level pressure) * (standard sea level temperature in K / air temperature in K). And TAS = EAS / SQRT (relative density). Relative density is normally written as sigma.

G

gamma is the diatomic gas constant, 1.4

R is the gas constant for dry air - 287 kJ/kg.K

T is the temperature in Kelvin.

50 degrees C is 323.15 Kelvin.

SQRT (1.4 x 287 x 323.15) = 360 m/s.

If you prefer knots, divide by 0.5144

And you get c = 700 knots.

If you have a local True Airspeed, divide that by c, and you get the Mach number. So, say you are flying at 500 knots TAS, in an air mass at 50deg.C, then your Mach number is 500/700 = 0.714.

Don't forget that if you are working in IAS or EAS, you need to make further conversions - and in particular at non ISA temperatures, even at sea level, you need to correct the EAS/TAS relationship for density altitude. Ideal gas laws are your friend again here.

So relative density = (pressure / standard sea level pressure) * (standard sea level temperature in K / air temperature in K). And TAS = EAS / SQRT (relative density). Relative density is normally written as sigma.

G

Join Date: May 1999

Location: Quite near 'An aerodrome somewhere in England'

Posts: 25,010

Assuming ISA, +10C static air temp would be at 2525 ft pressure altitude - a TAS of 500KTAS would mean M0.763.

M0.763 at the same pressure altitude at +50C static air temp would imply ISA+40C and would require a TAS of 535KTAS.

Mach No. is the actual TAS divided by the local speed of sound.

Keeping it all simple, TAS = Mach No. x 38.97 x √ absolute static air temp

M0.763 at the same pressure altitude at +50C static air temp would imply ISA+40C and would require a TAS of 535KTAS.

Mach No. is the actual TAS divided by the local speed of sound.

Keeping it all simple, TAS = Mach No. x 38.97 x √ absolute static air temp

*Last edited by BEagle; 9th Dec 2018 at 12:09.*

Join Date: Oct 2007

Location: Here

Posts: 467

If I recall correctly (its been loooong time) the underlying process behind this is quite simple.

Temperature is a measure of the kinetic energy of the motion of the atoms (well, molecules for the gases that comprise air). Kinetic energy is proportional to the square of the velocity of the individual molecules.

E = 1/2 m V*V

Absolute zero is the point at which all motion ceases. This is why temperatures below that cannot exist.

The speed of sound is the result of the average time and distance that a gas molecule travels before bumping into another one. The hotter the gas, the faster the molecules are moving the less time that transpires before a molecule bumps into the next one and the faster the sound pressure wave travels.

Temperature is a measure of the kinetic energy of the motion of the atoms (well, molecules for the gases that comprise air). Kinetic energy is proportional to the square of the velocity of the individual molecules.

E = 1/2 m V*V

Absolute zero is the point at which all motion ceases. This is why temperatures below that cannot exist.

The speed of sound is the result of the average time and distance that a gas molecule travels before bumping into another one. The hotter the gas, the faster the molecules are moving the less time that transpires before a molecule bumps into the next one and the faster the sound pressure wave travels.

Join Date: Feb 2000

Location: UK

Posts: 13,484

G

Join Date: Nov 2005

Location: London

Posts: 513

S-Works

'We care' because somebody asked the question. That is the job at hand. Also, other people cared enough to figure it out hence you have been able to spend 10,000hrs in a cockpit unbothered by the know-how that made it all possible.

Why do we care? It’s not a calculation I have done in the cockpit in 10,000hrs. Perhaps we should

concentrate on the job at hand .....

concentrate on the job at hand .....

*Last edited by oggers; 26th Dec 2018 at 13:22.*