The aeroPerformanceMap contains a map with aerodynamic data of the complete aircraft in the form of nondimensional coefficients. The force coefficients in i-direction (ci) are nondimensionalized by dynamic pressure and reference area, the moment coefficients (cmi) by dynamic pressure, reference area and reference length.

All coefficients in the aeroPerformanceMap relate to the aerodynamic coordinate system which is deducted from the CPACS coordinate system by the transformations of angle of attack and angle of yaw. See the documentation of the CPACS element for further details.

The dependent parameters of the aeroPerformanceMap are altitude, machNumber, angleOfSideslip and angleOfAttack. These elements are vectors of equal length, where values with identical indices belong together. The solution vectors ci and cmi have the same length as the input vectors. Shown below is an example where with 10 values per vector:

<altitude mapType="vector">12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02</altitude>
<machNumber mapType="vector">0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2</machNumber>
<angleOfSideslip mapType="vector">0;0;0;0;0;2;2;2;2;2</angleOfSideslip>
<angleOfAttack mapType="vector">-2;0;2;4;6;-2;0;2;4;6</angleOfAttack>
<cd mapType="vector">0.056;0.094;0.132;0.17;0.208;0.072;0.11;0.148;0.186;0.224</cd>
<cs mapType="vector">0.;0.;0.;0.;0.;0.01;0.015;0.02;0.025;0.03</cs>
<cl mapType="vector">-0.1;0.04;0.18;0.32;0.46;-0.08;0.03;0.14;0.25;0.36</cl>

The aerodynamic coefficients for altitude=1200m, machNumber=0.2, angleOfSideslip=0° and angleOfAttack=6° can be found at the 5th index: cd=0.208, cs=0 and cl=0.46.