Functions
TiglReturnCode	tiglFuselageGetSegmentSurfaceArea (TiglCPACSConfigurationHandle cpacsHandle, int fuselageIndex, int segmentIndex, double *surfaceAreaPtr)
	Returns the surface area of a segment of a fuselage. More...

TiglReturnCode	tiglFuselageGetSurfaceArea (TiglCPACSConfigurationHandle cpacsHandle, int fuselageIndex, double *surfaceAreaPtr)
	Returns the surface area of the fuselage. Currently, the area includes also the faces on the fuselage symmetry plane (in case of a symmetric wing). This is in particular a problem for fuselages, where only one half side is defined in CPACS. In future releases, these faces will not belong anymore to the surface area calculation. More...

TiglReturnCode	tiglGetCrossSectionArea (TiglCPACSConfigurationHandle cpacsHandle, const char componentUID, double origin_x, double origin_y, double origin_z, double normal_x, double normal_y, double normal_z, double area)
	tiglGetCrossSectionArea returns the area of the intersection of either the fused aircraft or its component (via UID) with a plane. The function can be used for Whitcomb's area rule. If no intersections are found, the resulting area is zero. No warning or error is thrown in this case. If more than one intersection is found, the returned area is the sum of the areas of the intersections. No warning or error is thrown. In the case that the UID of the whole airplane is given, the airplane will be fused before the calculation of the intersections is performed. More...

TiglReturnCode	tiglWingGetReferenceArea (TiglCPACSConfigurationHandle cpacsHandle, int wingIndex, TiglSymmetryAxis symPlane, double *referenceAreaPtr)
	Returns the reference area of the wing. More...

TiglReturnCode	tiglWingGetSegmentLowerSurfaceAreaTrimmed (TiglCPACSConfigurationHandle cpacsHandle, int wingIndex, int segmentIndex, double eta1, double xsi1, double eta2, double xsi2, double eta3, double xsi3, double eta4, double xsi4, double *surfaceArea)
	Computes the area of the trimmed lower wing segment surface. This function can be e.g. used to determine the area of the wing flaps. More...

TiglReturnCode	tiglWingGetSegmentSurfaceArea (TiglCPACSConfigurationHandle cpacsHandle, int wingIndex, int segmentIndex, double *surfaceAreaPtr)
	Returns the surface area of a segment of a wing. This includes only the area of the upper and lower wing segment surface and does not include the trailing edge or any closing faces. More...

TiglReturnCode	tiglWingGetSegmentUpperSurfaceAreaTrimmed (TiglCPACSConfigurationHandle cpacsHandle, int wingIndex, int segmentIndex, double eta1, double xsi1, double eta2, double xsi2, double eta3, double xsi3, double eta4, double xsi4, double *surfaceArea)
	Computes the area of the trimmed upper wing segment surface. This function can be e.g. used to determine the area of the wing flaps. More...

TiglReturnCode	tiglWingGetSurfaceArea (TiglCPACSConfigurationHandle cpacsHandle, int wingIndex, double *surfaceAreaPtr)
	Returns the surface area of the wing. Currently, the area includes also the faces on the wing symmetry plane (in case of a symmetric wing). In coming releases, these faces will not belong anymore to the surface area calculation. More...

TiglReturnCode	tiglWingGetWettedArea (TiglCPACSConfigurationHandle cpacsHandle, const char wingUID, double wettedAreaPtr)
	Returns the wetted area of the wing. If the wing has no parent (fuselage), it returns the surface area of the wing. More...

Detailed Description

Function for surface area calculations of wings/fuselages.

Function Documentation

◆ tiglFuselageGetSegmentSurfaceArea()

TiglReturnCode tiglFuselageGetSegmentSurfaceArea	(	TiglCPACSConfigurationHandle	cpacsHandle,
		int	fuselageIndex,
		int	segmentIndex,
		double *	surfaceAreaPtr
	)

Returns the surface area of a segment of a fuselage.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	fuselageIndex	The index of a fuselage, starting at 1
[in]	segmentIndex	The index of a segment, starting at 1
[out]	surfaceAreaPtr	The pointer to a variable for the surface area of the fuselage-segment

Returns

TIGL_SUCCESS if no error occurred
TIGL_NOT_FOUND if no configuration was found for the given handle
TIGL_INDEX_ERROR if fuselageIndex, sectionIndex or elementIndex are not valid
TIGL_NULL_POINTER if surfaceAreaPtr is a null pointer
TIGL_ERROR if some other error occurred

◆ tiglFuselageGetSurfaceArea()

TiglReturnCode tiglFuselageGetSurfaceArea	(	TiglCPACSConfigurationHandle	cpacsHandle,
		int	fuselageIndex,
		double *	surfaceAreaPtr
	)

Returns the surface area of the fuselage. Currently, the area includes also the faces on the fuselage symmetry plane (in case of a symmetric wing). This is in particular a problem for fuselages, where only one half side is defined in CPACS. In future releases, these faces will not belong anymore to the surface area calculation.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	fuselageIndex	Index of the Fuselage to calculate the area, starting at 1
[out]	surfaceAreaPtr	The surface area of the wing

Returns

TIGL_SUCCESS if no error occurred
TIGL_NOT_FOUND if no configuration was found for the given handle
TIGL_INDEX_ERROR if fuselageIndex is less or equal zero
TIGL_ERROR if some other error occurred

◆ tiglGetCrossSectionArea()

TiglReturnCode tiglGetCrossSectionArea	(	TiglCPACSConfigurationHandle	cpacsHandle,
		const char *	componentUID,
		double	origin_x,
		double	origin_y,
		double	origin_z,
		double	normal_x,
		double	normal_y,
		double	normal_z,
		double *	area
	)

tiglGetCrossSectionArea returns the area of the intersection of either the fused aircraft or its component (via UID) with a plane. The function can be used for Whitcomb's area rule. If no intersections are found, the resulting area is zero. No warning or error is thrown in this case. If more than one intersection is found, the returned area is the sum of the areas of the intersections. No warning or error is thrown. In the case that the UID of the whole airplane is given, the airplane will be fused before the calculation of the intersections is performed.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	componentUID	UID of a geometric component or the whole plane
[in]	origin_x	x-component of the origin of the plane
[in]	origin_y	y-component of the origin of the plane
[in]	origin_z	z-component of the origin of the plane
[in]	normal_x	x-direction of the normal of the plane
[in]	normal_y	y-direction of the normal of the plane
[in]	normal_z	z-direction of the normal of the plane
[out]	area	The area of the intersection of the aircraft with the plane

Returns

TIGL_SUCCESS if no error occurred
TIGL_MATH_ERROR if the normal of the plane is zero
TIGL_ERROR if some other error occurred

◆ tiglWingGetReferenceArea()

TiglReturnCode tiglWingGetReferenceArea	(	TiglCPACSConfigurationHandle	cpacsHandle,
		int	wingIndex,
		TiglSymmetryAxis	symPlane,
		double *	referenceAreaPtr
	)

Returns the reference area of the wing.

The reference area of the wing is calculated by taking account the quadrilateral portions of each wing segment by projecting the wing segments into the plane defined by the user. If projection should be avoided, use TIGL_NO_SYMMETRY as symPlane argument.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	wingIndex	Index of the Wing to calculate the area, starting at 1
[in]	symPlane	Plane on which the wing is projected for calculating the refarea. Values can be: TIGL_NO_SYMMETRY, the wing is not projected but its true 3D area is calculated TIGL_X_Y_PLANE, the wing is projected onto the x-y plane (use for e.g. main wings and HTPs) TIGL_X_Z_PLANE, the wing is projected onto the x-z plane (use for e.g. VTPs) TIGL_Y_Z_PLANE, the wing is projected onto the y-z plane
[out]	referenceAreaPtr	The reference area of the wing

Returns

TIGL_SUCCESS if no error occurred
TIGL_NOT_FOUND if no configuration was found for the given handle
TIGL_INDEX_ERROR if wingIndex is less or equal zero
TIGL_ERROR if some other error occurred

◆ tiglWingGetSegmentLowerSurfaceAreaTrimmed()

TiglReturnCode tiglWingGetSegmentLowerSurfaceAreaTrimmed	(	TiglCPACSConfigurationHandle	cpacsHandle,
		int	wingIndex,
		int	segmentIndex,
		double	eta1,
		double	xsi1,
		double	eta2,
		double	xsi2,
		double	eta3,
		double	xsi3,
		double	eta4,
		double	xsi4,
		double *	surfaceArea
	)

Computes the area of the trimmed lower wing segment surface. This function can be e.g. used to determine the area of the wing flaps.

The use of this function is analog to tiglWingGetSegmentUpperSurfaceAreaTrimmed.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	wingIndex	The index of a wing, starting at 1
[in]	segmentIndex	The index of a segment, starting at 1
[in]	eta1	Eta value of P1 in range [0,1]
[in]	xsi1	Xsi value of P1 in range [0,1]
[in]	eta2	Eta value of P2 in range [0,1]
[in]	xsi2	Xsi value of P2 in range [0,1]
[in]	eta3	Eta value of P3 in range [0,1]
[in]	xsi3	Xsi value of P3 in range [0,1]
[in]	eta4	Eta value of P4 in range [0,1]
[in]	xsi4	Xsi value of P4 in range [0,1]
[out]	surfaceArea	Area of the trimmed lower wing surface

Returns

TIGL_SUCCESS if no error occurred
TIGL_NOT_FOUND if no configuration was found for the given handle
TIGL_INDEX_ERROR if wingIndex ot segmentIndex are not valid
TIGL_NULL_POINTER if surfaceArea is a null pointer
TIGL_ERROR if the eta/xsi coordinates are not in the valid range [0,1] or another error occurred

◆ tiglWingGetSegmentSurfaceArea()

TiglReturnCode tiglWingGetSegmentSurfaceArea	(	TiglCPACSConfigurationHandle	cpacsHandle,
		int	wingIndex,
		int	segmentIndex,
		double *	surfaceAreaPtr
	)

Returns the surface area of a segment of a wing. This includes only the area of the upper and lower wing segment surface and does not include the trailing edge or any closing faces.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	wingIndex	The index of a wing, starting at 1
[in]	segmentIndex	The index of a segment, starting at 1
[out]	surfaceAreaPtr	The pointer to a variable for the surface area of the wing

Returns

TIGL_SUCCESS if no error occurred
TIGL_NOT_FOUND if no configuration was found for the given handle
TIGL_INDEX_ERROR if wingIndex, sectionIndex or elementIndex are not valid
TIGL_NULL_POINTER if surfaceAreaPtr is a null pointer
TIGL_ERROR if some other error occurred

◆ tiglWingGetSegmentUpperSurfaceAreaTrimmed()

TiglReturnCode tiglWingGetSegmentUpperSurfaceAreaTrimmed	(	TiglCPACSConfigurationHandle	cpacsHandle,
		int	wingIndex,
		int	segmentIndex,
		double	eta1,
		double	xsi1,
		double	eta2,
		double	xsi2,
		double	eta3,
		double	xsi3,
		double	eta4,
		double	xsi4,
		double *	surfaceArea
	)

Computes the area of the trimmed upper wing segment surface. This function can be e.g. used to determine the area of the wing flaps.

The computed area does not include the trailing edge or any closing side faces.

All eta and xsi values must be in the range [0,1]. The trimmed area is defined with the four corner point P1, P2, P3, and P4. The order of the points should be right handed, as shown the the image below.

Location of the four corner points

Each of the points is defined with an eta/xsi coordinate pair in the wing segment system.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	wingIndex	The index of a wing, starting at 1
[in]	segmentIndex	The index of a segment, starting at 1
[in]	eta1	Eta value of P1 in range [0,1]
[in]	xsi1	Xsi value of P1 in range [0,1]
[in]	eta2	Eta value of P2 in range [0,1]
[in]	xsi2	Xsi value of P2 in range [0,1]
[in]	eta3	Eta value of P3 in range [0,1]
[in]	xsi3	Xsi value of P3 in range [0,1]
[in]	eta4	Eta value of P4 in range [0,1]
[in]	xsi4	Xsi value of P4 in range [0,1]
[out]	surfaceArea	Area of the trimmed upper wing surface

Returns

TIGL_SUCCESS if no error occurred
TIGL_NOT_FOUND if no configuration was found for the given handle
TIGL_INDEX_ERROR if wingIndex ot segmentIndex are not valid
TIGL_NULL_POINTER if surfaceArea is a null pointer
TIGL_ERROR if the eta/xsi coordinates are not in the valid range [0,1] or another error occurred

◆ tiglWingGetSurfaceArea()

TiglReturnCode tiglWingGetSurfaceArea	(	TiglCPACSConfigurationHandle	cpacsHandle,
		int	wingIndex,
		double *	surfaceAreaPtr
	)

Returns the surface area of the wing. Currently, the area includes also the faces on the wing symmetry plane (in case of a symmetric wing). In coming releases, these faces will not belong anymore to the surface area calculation.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	wingIndex	Index of the Wing to calculate the area, starting at 1
[out]	surfaceAreaPtr	The surface area of the wing

Returns

TIGL_SUCCESS if no error occurred
TIGL_NOT_FOUND if no configuration was found for the given handle
TIGL_INDEX_ERROR if wingIndex is less or equal zero
TIGL_ERROR if some other error occurred

◆ tiglWingGetWettedArea()

TiglReturnCode tiglWingGetWettedArea	(	TiglCPACSConfigurationHandle	cpacsHandle,
		const char *	wingUID,
		double *	wettedAreaPtr
	)

Returns the wetted area of the wing. If the wing has no parent (fuselage), it returns the surface area of the wing.

Parameters

[in]	cpacsHandle	Handle for the CPACS configuration
[in]	wingUID	UID of the Wing to calculate the wetted area
[out]	wettedAreaPtr	The wetted area of the wing

Returns

TIGL_SUCCESS if no error occurred
TIGL_NOT_FOUND if no configuration was found for the given handle
TIGL_UID_ERROR if wingUID is wrong
TIGL_NULL_POINTER if wingIUD is NULL
TIGL_ERROR if some other error occurred

Functions

Detailed Description

Function Documentation

◆ tiglFuselageGetSegmentSurfaceArea()

◆ tiglFuselageGetSurfaceArea()

◆ tiglGetCrossSectionArea()

◆ tiglWingGetReferenceArea()

◆ tiglWingGetSegmentLowerSurfaceAreaTrimmed()

◆ tiglWingGetSegmentSurfaceArea()

◆ tiglWingGetSegmentUpperSurfaceAreaTrimmed()

◆ tiglWingGetSurfaceArea()

◆ tiglWingGetWettedArea()