ROTORS WITH TRAILING-EDGE FLAPS - ANALYSIS AND COMPARISON WITH EXPERIMENTAL-DATA

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 co mprehensive analysis, Correlation between predicted and measured frequ encies is generally fair. The forward flight trim control predictions also show fair correlation. For the baseline rotor with no trailing ed ge flap motion, overall correlation of blade bending and torsional mom ents is fair. Significant discrepancies are observed in 3/rev inplane bending. With trailing edge flap moving +/-4 degrees at 5/rev, the ana lysis overpredicts the 5/rev flatwise bending moments due to the flap motion, while the the blade torsional moment is predicted fairly well. Varying the phase angle of the flap motion had a significant effect o n the blade 4/rev flatwise and inplane bending loads. The computationa l results were found to be sensitive to variations in the modeling dat a.