Cold-air Performance of a 12.766-centimeter-tip-diameter Axial-flow Cooled Turbine


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A solid blade version of a single-stage, axial-flow turbine was investigated to determine its performance over a range of speeds from 0 to 105 percent of equivalent design speed and over a range of total to static pressure ratios from 1.62 to 5.07.







NASA Technical Paper


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NASA Technical Paper


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NASA Technical Note


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R & D Abstracts


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Government Reports Annual Index


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Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.