Engineering, 21.08.2019 05:20, helpplz84

Tests on an axial compressor revealed that the relative mach number at thee rotor inlet as 0.7 when the flow coefficient was 0.5. the flow angle exiting the rotor is 300 from the axial direction and the velocity triangles are symmetric at the blade mean radius. if the inlet stagnation temperature is 289 k, determine the stagnation temperature rise obtained under the above conditions

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Tests on an axial compressor revealed that the relative mach number at thee rotor inlet as 0.7 when...