A cooperative program, undertaken by organizations in the United States, England, France, and Australia, assessed the strengths and weaknesses of four lifting-line/wake methods and three CFD methods by comparing their predictions with the data obtained in flight trials of a research Puma. The Puma has been tested in two configurations: a mixed-bladed rotor with instrumented rectangular-tip and swept-tip blades, and a configuration with four identical swept-tip blades. The present paper examines the results of the lifting-line predictions. The better lifting-line methods show good agreement with lift at the blade tip for the configuration with four swept tips; the moment is well-predicted at 0.92 R, but deteriorates outboard. The predictions for the mixed-bladed rotor configuration range from fair to good. The lift prediction is better for the swept-tip blade than for rectangular-tip blade, but the reasons for this cannot be determined because of the unmodeled effects of the mixed-bladed rotor. Keywords: Helicopter flight test; Computational fluid dynamics; Helicopter airloads correlation; Helicopter rotors; Rotor blades rotary wings. (edc)
Correlation of Puma Airloads-Lifting-Line and Wake Calculation
1989
30 pages
Report
No indication
English
Aerodynamics , Aircraft , Aerodynamic loading , Blade tips , Helicopter rotors , Aerodynamic lift , Rotor blades(Rotary wings) , Wake , Australia , Computations , Aerodynamic configurations , Correlation , Flight testing , Fluid dynamics , France , Great Britain , Helicopters , Inflight , Mathematical prediction , Research aircraft , United States , Mixed bladed helicopter rotor blades , Lifting line , Computational fluid dynamics , Puma aircraft , Swept blade tips(Rotor blades)
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