Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 4: modification of aerodynamic design and prediction of performance
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Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 4: modification of aerodynamic design and prediction of performance, report, June 1955; (https://digital.library.unt.edu/ark:/67531/metadc61343/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.