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Across the normal shockwave: 1) Stagnation pressure decreases whereas stagnation temperature remains constant 2) Mach number before the shockwave is always greater than one and after the shockwave, the Mach number need not be less than one 3) Across the shockwave there is a rise in pressure and temperature 4) The product of Mach number downstream of normal shockwave and upstream of normal shockwaves always one Which of the above statements are correct?
Statement (I) : Mass flow through the convergent nozzle is maximum when the exit Mach number is 1. Statement (II) : The divergent section is added to convergent nozzle to increase the exit Mach number and not to increase the mass flow rate
The Mach number for hypersonic flow of compressible fluid is
For hypersonic flow, the Mach number is
Mach number is defined as the ratio of the local flow velocity to the sonic velocity in the fluid. For what value of Mach number, the gases are considered incompressible?
For which of these Mach numbers is flow considered to be hypersonic?
work on hypersonic bodies involves testing Mach number, Reynolds number and temperature simultaneously.
What is the Mach number of Hypersonic Aircraft?
There are two rows, each containing 3 numbers. Below are some rules to be used to get the resultant number for each row separately. Use the rule from left to right for each row and find the answer to the question. Rule: 1. If an even number is followed by an even number, then the first number will be subtracted from the second. 2. If an odd number is followed by an odd number, then both will be added. 3. If an odd number is followed by an even number, then the even number will be subtracted from the square of the odd number. 4. If an even number is followed by an odd number, then the odd number will be subtracted from the even number. Row I: 9,11, 34 Row II: 16, 9, 8 What is the difference between the resultant numbers in the first row and the second row
The characteristic Mach number and Mach number are related. Which of these is not correct?