Research sponsered by NASA has indicated that there is a significant potential for fuel savings from 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 10x10 foot wind tunnel had variations in the level of airfoil technology and acitivity 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 8x6 foot wind tunnel. Results from these tests show high propell er performance can be obtained to at least Mach 0.8, offering the potential of reducing trip fuel by 15 to 30 % compares to equivalent technology high bypass ratio turbofans. (Wassmann)
Low and high speed propellers for general aviation - performance, potential and recent wind tunnel test results
Niedrig- und Hochgeschwindigkeitspropeller fuer die Zivilluftfahrt - Leistung, Moeglichkeiten und neue Versuchsergebnisse aus dem Windkanal
SAE Papers. Cumulative Index ; 1-13
1981
13 Seiten, 17 Bilder, 2 Tabellen, 24 Quellen
Aufsatz (Konferenz)
Englisch
SAE Technical Papers | 1981
|Wind Tunnel Testing of High Speed Propellers
British Library Conference Proceedings | 1997
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