The design of an airplane is modified to increase the vertical tail area by $20 \%$ and decrease the moment arm from the aerodynamic centre of the vertical tail to the airplane centre of gravity by $20 \% .$ Assuming all other factors remain unchanged, the ratio of the modified to the original directional static stability ( $C_{N_{\beta}}$ due to tail fin) is____________ (round off to 2 decimal places).

The design of an airplane is modified to increase the vertical tail area by $20 \%$ and decrease the moment arm from the aerodynamic centre of the vertical tail to the airplane centre of gravity by $20 \% .$ Assuming all other factors remain unchanged, the ratio of the modified to the original directional static stability ( $C_{N_{\beta}}$ due to tail fin) is____________ (round off to 2 decimal places).

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