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10-54. 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: Finite Equivalent Plate, Element Freq. Cycle/s 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. 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: Finite Equivalent Plate, Element Freq. Cycle/s 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.

MATLAB: An Introduction with Applications
MATLAB: An Introduction with Applications
6th Edition
ISBN:9781119256830
Author:Amos Gilat
Publisher:Amos Gilat
Chapter1: Starting With Matlab
Section: Chapter Questions
Problem 1P
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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: Finite Equivalent Plate, Cycle/s Element Freq. Cycle/s 1 14.58 14.76 48.52 49.10 3 97.22 99.99 4 113.99 117.53 5 174.73 181.22 212.72 220.14 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.
Transcribed Image Text: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: Finite Equivalent Plate, Cycle/s Element Freq. Cycle/s 1 14.58 14.76 48.52 49.10 3 97.22 99.99 4 113.99 117.53 5 174.73 181.22 212.72 220.14 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.
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