Question

An article in the Journal of Aircraft (1986, Vol. 23, pp. 859-864) described a new equivalent plate analysis method formulation that is capable of modeling aircraft structures such as cranked wing boxes and that produces results similar to the more computationally intensive finite element analysis method. Natural vibration frequencies for the cranked wing box structure are calculated using both methods, and results for the first seven natural frequencies are the following: Finite 14.58 48.52 97.22 113.99 174.73 212.72 277.38 and Equivalent 14.76 49.1 99.99 117.53 181.22 220.14 294.8 .

(a) Test the assumptions

(b) Do the data suggest that the two methods provide the same mean value for natural vibration frequency? Use α = 0.05. Find the P-value.

(c) Find a 95% confidence interval on the mean difference between the two methods

Answer 1

Finite	Equi	d
14.58	14.76	-0.18
48.52	49.1	-0.58
97.22	99.99	-2.77
113.99	117.53	-3.54
174.73	181.22	-6.49
212.72	220.14	-7.42
277.38	294.8	-17.42
		-5.486	MEAN
		5.924	Stdev