Low and High Speed Propellers for General Aviation Performance Potential and Recent Wind Tunnel Test Results National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH

Format:

Conference/Event

Author/Creator:

Jeracki, Robert J., author.

Conference Name:

Aerospace Congress & Exposition (1981-10-05 : Anaheim, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1981

Summary:

Research sponsored by NASA has indicated that there is a significant potential for fuel savings from advanced propellers designed for lower speed general aviation (G.A.) aircraft as well as the advanced turboprop for future higher speed (Mach 0.6 to 0.8) aircraft. Lower speed G.A. propellers tested in the Lewis 1010 foot wind tunnel had variations in the level of airfoil technology and activity factor. At cruise, the measured performance was about 4 to 5% below the predicted levels. A large part of this difference appears to be from inadequate modeling of blade and spinner losses with round shank blade designs. Blade cuffs and shaping of the spinner/blade juncture should offer the potential of recovering most of these losses, and combined with various advanced concepts may result in a 10 to 15% reduction in trip fuel for future lower speed G.A. aircraft. Advanced aerodynamic concepts for high cruise speeds were evaluated in the Lewis 86 foot wind tunnel. Results from these tests show high propeller performance can be obtained to at least Mach 0.8, offering the potential of reducing trip fuel by 15 to 30% compared to equivalent technology high bypass ratio turbofans

Notes:

Vendor supplied data

Publisher Number:

811090

Access Restriction:

Restricted for use by site license