It can be calculated at any altitude - including negative ones - eg under water.
Critical Mach Number has nothing (directly) to do with altitude. Mach Number has everything to do Temperature,
Mach number is dependent on a number of factors. Factors such as air density or altitude will change the Mach number. At approximatively 45 000 ft Mach 0.85 =289.2361 m/s = 1041.25 km/h = 647.0028 mph
It depends on altitude and humidity Mach I is about 1,225 kilometers per hour.
At 30,000 feet, Mach 1 is approximately 661.7 miles per hour (1,070 kilometers per hour). This speed can vary slightly based on temperature and atmospheric conditions, as Mach number is defined relative to the speed of sound, which decreases with altitude due to lower temperatures. At this altitude, the temperature is typically around -30°C (-22°F), affecting the speed of sound.
Ernst Mach .
Critical Mach Number has nothing (directly) to do with altitude. Mach Number has everything to do Temperature,
Mach number is dependent on a number of factors. Factors such as air density or altitude will change the Mach number. At approximatively 45 000 ft Mach 0.85 =289.2361 m/s = 1041.25 km/h = 647.0028 mph
Mach 3.3 is about 2,512 mph depending on altitude.
no mach no is defined as ratio of local speed of aeroplane to speed of sound. As the altitude increases the True speed of aeroplane increases and speed of sound decreases because of reduction of ambient temperature Hence the value of their ratio should increase at an increasing rate with increase in altitude. Keeping the Mach No constant say, 2 means reduction of speed to a large extent so as to maintain constant Mach No. Therefore same Mach no the aeroplane at higher altitude is flying slower
MACH NUMBER can be calculated by dividing the spped of an object by its local speed of soundTo convert it into metre multiply it with the speed of sound. For example, to convert 0.8 mach into metre , 0.8 with 343 gives 274.4 m/s.
the Mach number
no. it's top speed was calculated to only be mach 3.5
More than Mach 2 at its premium altitude.
It depends on altitude and humidity Mach I is about 1,225 kilometers per hour.
True airspeed (TAS) can be calculated from calibrated airspeed (CAS) by applying the compressibility correction factor based on altitude and temperature. The Mach number (MN) can be used to adjust the calculated TAS to account for the effects of speed of sound at the given conditions. TAS is typically calculated using the formulas provided in aviation manuals or with the help of specialized flight computers.
Ernst Mach .
That all depends on the altitude the mach speed is occurring at. Mach 1 is defined as the speed of sound which is a function of fluid density. In air at sea level and normal temperature, 0.85 mach = ~647 mph 0.85mach ~.(0.85*330)mph