An Investigation of the Effect of Blade Curvature on Centrifugal-Impeller Performance Page: 13 of 25
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NACA TN No. 1313
5. Impeller B had the largest useful operating range at a pros-
sure ratio of 1.80; impeller A had the largest useful operating range
between pressure ratios of 2.20 to 3.00; and imleller C had the
smallest useful operating range at all preesure ratios.
6. Impellers B and C exhibited an operational instability at
high equivalent tip speeds near the maximum specific capacity.
Flight Propulsion Research Laboratory,
National Advisory Committee for Aeronautics,
Cleveland, Ohio, FGbruary 21, 1947.
REFERENCES
1. Ritter, Williamn K., and Johnsen, Irving A.: Preliminary Investi-
gation of Deeoop Inducers as Separate Supercharger Components.
NACA AER No. E5128, 1945.
2. Ritter, William K., Gineburg, Ambrose, and Boedo, William L.:
Performance Comparison of Two Deap Inducers as Separate Components
and in Combination with an Impollor. NACA ARR No. E5JOZ, 1945.
3. Ellerbrock, He:rman H, Jr., and Goldstein, Arthur W.: Principles
and Methods of Bating and Testing Centrifugal Superchargers.
NACA A.PRE, Feb. 1942.
4. Hottle, H. C., and Ke.litinsky, A.: Temperature Measuroments in
High-Velocity Air Streams. Jour. Appl. Meoob., vol. 12, no. 1,
March 1945, pp. A25-A32.
5. NACA Subcommittee on Supercharger Compressors: Standard Methgd
of Graphical Presentation of Centrifugal Compressor Performance.
NACA ARR No. E5FI3a, 1945.12
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Anderson, Robert J.; Ritter, William K. & Dildine, Dean M. An Investigation of the Effect of Blade Curvature on Centrifugal-Impeller Performance, report, May 1947; (https://digital.library.unt.edu/ark:/67531/metadc55452/m1/13/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.