Flutter Boundary Prediction Based on Structural Frequency Response Functions Acquired from Ground Test

Table 1

Three lowest-order mode frequencies of the wing.

Order	Normal state (Hz)		Leading state (Hz)		Trailing state (Hz)		Mode shape
	FEM	Test	FEM	Test	FEM	Test
1	16.48	16.46	15.50	15.55	15.50	15.56	1st bending mode
2	47.35	47.38	43.16	43.28	43.16	43.27	1st torsional mode
3	101.75	101.13	98.94	98.48	98.94	98.52	2nd bending mode