Accession Number:

AD0256531

Title:

SHROUDED PROPELLER INVESTIGATIONS: WIND TUNNEL TESTS OF A 4-BLADED SHROUDED PROPELLER MODEL HAVING A 0.30 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 two variable pitch blades operating within a 0.50 chorddiameter ratio shroud. 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 non-diffused exit. Seven exit vanes designed to remove the rotational component of jet velocity at design conditions were installed. The centerbody of the model had a 0.3 hubtip diameter ratio. 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 at forward flight conditions, and with propeller tip speed at static flight conditions. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE