10-54. O 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 struc- ture are calculated using both methods, and results for the first seven natural frequencies follow: Equivalent Plate, Cycle/s Finite Element Freq. Cycle/s 14.58 14.76 2 48.52 49.10 3 97.22 99.99 4 113.99 117.53 5 174.73 181.22 6 212.72 220.14 7 277.38 294.80 (a) Do the data suggest that the two methods provide the same mean value for natural vibration frequency? Use a = 0.05. Find the P-value. (b) Find a 95% confidence interval on the mean difference between the two methods.
10-54. O 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 struc- ture are calculated using both methods, and results for the first seven natural frequencies follow: Equivalent Plate, Cycle/s Finite Element Freq. Cycle/s 14.58 14.76 2 48.52 49.10 3 97.22 99.99 4 113.99 117.53 5 174.73 181.22 6 212.72 220.14 7 277.38 294.80 (a) Do the data suggest that the two methods provide the same mean value for natural vibration frequency? Use a = 0.05. Find the P-value. (b) Find a 95% confidence interval on the mean difference between the two methods.
Algebra & Trigonometry with Analytic Geometry
13th Edition
ISBN:9781133382119
Author:Swokowski
Publisher:Swokowski
Chapter3: Functions And Graphs
Section3.3: Lines
Problem 76E
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