A comprehensive aeroelastic analysis is developed to investigate plain trailing edge flaps for vibration control. Results from the analysis are compared with experimental wind tunnel data and that of another comprehensive analysis. Correlation between predicted and measured frequencies is generally fair. The forward flight trim control predictions also show fair correlation. For the baseline rotor with no trailing edge flap motion, overall correlation of blade bending and torsional moments is fair. Significant descrepancies are observed in 3/rev inplane bending. While trailing edge flap moving +/-4 deg of angle at 5/rev, the analysis overpredicts the 5/rev flatwise bending moments due to the flap motion, while the blade torsional moment is predicted fairly well. Varying the phase angle of the flap motion had a significant effect on the blade 4/rev flatwise and inplane bending loads. The computational results were found to be sensitive to variations in the modeling data.
Rotors with trailing edge flaps: Analysis and comparison with experimental data
Hubschrauberrotoren mit Vorderkantenklappen: Analyse und Vergleich mit Meßdaten
Journal of the American Helicopter Society ; 43 , 4 ; 319-332
1998
14 Seiten, 26 Bilder, 3 Tabellen, 27 Quellen
Aufsatz (Zeitschrift)
Englisch
Rotors With Trailing Edge Flaps: Analysis and Comparison With Experimental Data
Online Contents | 1998
|Comprehensive modeling of rotors with trailing edge flaps
Tema Archiv | 1999
|Aeroelastic analysis of rotors with trailing edge flaps using comprehensive codes
Tema Archiv | 2001
|Aeroelastic Analysis of Rotors with Trailing Edge Flaps Using Comprehensive Codes
Online Contents | 2001
|Engineering Index Backfile | 1937
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