aeroPerformanceMapType Complex Type

Aerodynamic coefficients and derivatives

Namespace: Empty

Schema: Empty

Base Type

complexBaseType

Usages

aeroPerformanceMap

Children

Name	Occurrences	Description
All
altitude		Altitude [m]
angleOfAttack		Angle of attack [deg]
angleOfSideslip		Sideslip angle [deg]
cd	[0, 1]	Drag coefficient in aerodynamic coordinates
cl	[0, 1]	Lift coefficient in aerodynamic coordinates
cmd	[0, 1]	Aerodynamic moment around d-axis of the aerodynamic coordinate system
cml	[0, 1]	Aerodynamic moment around l-axis of the aerodynamic coordinate system
cms	[0, 1]	Aerodynamic moment around s-axis of the aerodynamic coordinate system
cs	[0, 1]	Coefficient of the side force vector in aerodynamic coordinates (perpendicular to lift and drag)
dampingDerivatives	[0, 1]	Damping derivatives with respect to the rotational rates
incrementMaps	[0, 1]	Increments of the aerodynamic coefficients due to movable device deflections
machNumber		Mach number

Attributes

Name	Type	Description
externalDataDirectory	string	Directory of the external data file
externalDataNodePath	string	Path of the node inside the external data file
externalFileName	string	Name of the external data file

Remarks

Description

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:

Example aeroPerformanceMap

Copy

<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.