For a Selected Aircraft Stability and Control Characteristics Research and Calculation

Selecting the aircraft, Determining the necessary parameters for the stability and control calculation and finding the numerical values of these parameters for the aircraft, Static stability calculation, Dynamic stability calculation and reporting of results

EXAMPLE ( LIKE THIS)

\begin{tabular}{||c|c|c|c|c|c||} \hline Condition & 2 & 5 & 7 & 9 & 10 \\ \hline \hlineh(ft) & SL & 20,000 & 20,000 & 40,000 & 40,000 \\ M & 0.25 & 0.500 & 0.800 & 0.800 & 0.900 \\ ( degrees ) & 5.70 & 6.80 & 0.0 & 4.60 & 2.40 \\ W(lbf) & 564,032. & 636,636. & 636,636. & 636,636. & 636,636. \\ Ix( slug-t. 2) & 14.3106 & 18.4106 & 18.2106 & 18.2106 & 18.2106 \\ Iz( slug- 22) & 45.3106 & 49.5106 & 49.7106 & 49.7106 & 49.7106 \\ Ixz( slug-ft 2) & 2.23106 & 2.76106 & 0.97106 & 1.56106 & .35106 \\ \hline Cy & -.96 & -.90 & -.81 & -.88 & -.92 \\ Cl & -.221 & -.193 & -.164 & -.277 & -.095 \\ Cn & 0.150 & 0.147 & 0.179 & 0.195 & 0.207 \\ Clp & -.45 & -.323 & -.315 & -.334 & -.296 \\ Cnp & -.121 & -.0687 & 0.0028 & -.0415 & 0.0230 \\ Clr & 0.101 & 0.212 & 0.0979 & 0.300 & 0.193 \\ Cnr & -.30 & -.278 & -.265 & -.327 & -.333 \\ Cssa & 0.0461 & 0.0129 & 0.0120 & 0.0137 & 0.0139 \\ Cna & 0.0064 & 0.0015 & 0.0008 & 0.0002 & -.0027 \\ Cysr & 0.175 & 0.1448 & 0.0841 & 0.1157 & 0.0620 \\ Clr & 0.007 & 0.0039 & 0.0090 & 0.0070 & 0.0052 \\ Cnr & -.109 & -.1081 & -.0988 & -.1256 & -.0914 \\ \hline \end{tabular}