SHROUDED PROPELLER INVESTIGATIONS: WIND TUNNEL TESTS OF A 4-BLADED SHROUDED PROPELLER MODEL HAVING A 0.30 HUB/TIP DIAMETER RATIO CENTERBODY
Abstract
Wind tunnel tests have been conducted on a shrouded propeller model with two variable pitch blades operating within a 0.50 chord/diameter 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 hub/tip 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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1961
- Accession Number
- AD0256531
Entities
People
- Vernon O. Hoehne
Organizations
- Wichita State University