Accession Number:

AD0256532

Title:

SHROUDED PROPELLER INVESTIGATIONS: WIND TUNNEL TESTS OF A 4-BLADED SHROUDED PROPELLER MODEL HAVING A 0.4 HUB/TIP DIAMETER RATIO CENTERBODY

Descriptive Note:

Corporate Author:

WICHITA STATE UNIV KANS

Personal Author(s):

Report Date:

1961-03-01

Pagination or Media Count:

1.0

Abstract:

Wind tunnel tests have been conducted on a shrouded propeller model with four variable pitch blades operating within a 0.50 chorddiameter ratio shroud and having a 0.4 hubtip diameter ratio centerbody. The shroud had provisions for changing the inlet configuration from a streamlined or high-speed shape to a flared or bellmouth shape and for mounting either a diffused or nondiffused exit. Seven exit vanes designed to remove the rotational component of jet velocity at design conditions were installed. The design of the propeller blades was identical to the design of the blades used in a model having a 0.3 hubtip dia eter ratio centerbody. A comparison of the test data from these two models shows the effect of centerbody size on shrouded propeller performance. Performance of the model was measured throughout a range of advance ratios from zero to 2.2 at several blade pitch settings and angles of attack between zero and 90 degrees. Results are presented in the form of force and moment coefficients varying with power coefficient for forward flight conditions and with propeller rotation speed and static disc loading at zero speed conditions. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE