ABSTRAK :
The stability of an aircraft is very important in aircraft design. The stability analysis of the aircraft is aim to determine the static and dynamic stability of the aircraft. It consists of static stability of the lateral, the directional, the crosswind criterion, the spin recovery criteria, the dynamic stability and the flying qualities.
Stability analysis of the lateral directional is using digital datcom. Digital datcom software will provide the output of aerodynamic parameters such as Cl, Cn, Cy and derivatives. The aerodynamic parameters are then processed using calculation software such as Ms. Excel, mathlab and mathcad are used to view STTA-12 MXA stability.
The calculation results for static stability of the lateral directional is stable, because the value of Clβ = -0,00003 / deg and Cnβ = 0,0862 / deg. In dynamic stability is stable, because the eigenvalues are on the left of the imaginary axis (roll and dutch roll), while for the spiral is on the right of the imaginary axis but its value close to zero. Flying quality is at level 1 which means it is clearly adequate for aircraft flying category. The crosswind criteria were performed at takeoff and landing at some altitudes consist of sea level, 7,054 ft and 14,219 ft and using only 80 percent rudder deflection. The result on landing accomplishes with the rudder deflection criteria, while the sea level takeoff does not accomplishes the criteria and its solution adds to the use of rudder deflection. The spin recovery criteria accomplishes the criteria with the availability of rudder deflection when the angle of attack’s more than 50 degrees.
Keywords : Lateral-Directional, Digital Datcom, Stability of Aircraft.
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