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10. An article in the Journal of Aircraft (Vol. 23, 1986, pp. 859-864) formulation that is capable of modeling aircraft structures such similar to the more computat Natural vibration frequencies using both methods, and result eq. Finite Element Cycle/s 14.58 48.52 97.22 113.99 174.73 212.72 Equivalent Plate, Cycle/s 14.76 49.10 99.99 117.53 181.22 220.14 Do the data suggest that the tw vibration frequency? Use a=0.C

10. An article in the Journal of Aircraft (Vol. 23, 1986, pp. 859-864) formulation that is capable of modeling aircraft structures such similar to the more computat Natural vibration frequencies using both methods, and result eq. Finite Element Cycle/s 14.58 48.52 97.22 113.99 174.73 212.72 Equivalent Plate, Cycle/s 14.76 49.10 99.99 117.53 181.22 220.14 Do the data suggest that the tw vibration frequency? Use a=0.C

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. An article in the Journal of Aircraft (Vol. 23, 1986, pp. 859-864) describes 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 follow: Freq. 1 2 3 4 5 6 7 Finite Element Cycle/s 14.58 48.52 97.22 113.99 174.73 212.72 277.38 Equivalent Plate, Cycle/s 14.76 49.10 99.99 117.53 181.22 220.14 294.80 Do the data suggest that the two methods prove the same mean value for natural vibration frequency? Use a=0.05.
Transcribed Image Text:10. An article in the Journal of Aircraft (Vol. 23, 1986, pp. 859-864) describes 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 follow: Freq. 1 2 3 4 5 6 7 Finite Element Cycle/s 14.58 48.52 97.22 113.99 174.73 212.72 277.38 Equivalent Plate, Cycle/s 14.76 49.10 99.99 117.53 181.22 220.14 294.80 Do the data suggest that the two methods prove the same mean value for natural vibration frequency? Use a=0.05.
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