The free Fuselage design policy is similar to the loop policy except that any cross-section may be placed anywhere along the design length of the Fuselage component. This includes the first and last cross-sections which means that depending on the location of these sections, the actual physical length of the part modeled may be nowhere near the same length specified in design. As long as the user ensures that at least one section is placed at the 0.0 and 1.0 length positions, the design length and physical length will be similar. Exceptions are when Skinning forces the surface to loft forward of the 0.0 X position or aft of the 1.0 X position. Uses for this design policy include shaping engine nacelles with flat inlet and exits to be defined as boundary conditions for flow solvers. Freeform geometries are another application. This tutorial demonstrates how to use the free design policy and an example case.
By changing the Fuselage design policy from monotonic to loop, the first cross-section is enforced to be at the same location as the final section at 1.0x design length. The final section is also forced to exactly match the design of the first section. This ensures that the component surface follows a user-defined loop and closes. Typical uses of this feature are to design “hollow” nacelles, rocket nozzles, tubes/pipes, or turbojet/fan engine station internals. This tutorial demonstrates how to apply the loop design policy to a Fuselage component and some of the important aspects of modeling this way.
Fuselage components may be closed at the nose or tail by leveraging end caps when the first or last cross-section is chosen to be open e.g., not a point or line. The user has access to several cap types including None, Flat, Round, Edge, and Sharp. If an open cross-section is chosen for an end section, applying caps ensures that the geometry is “watertight” and ready for analyses or tools that rely on solid geometries rather than surfaces. This tutorial demonstrates how to apply caps to a Fuselage component and how to adjust the cap tessellation.
This tutorial will demonstrate how to change the Fuselage cross-section type from one to another. Note that a Fuselage cross-section may be any of the available types in OpenVSP, including airfoils, but that the implementation and placement of the section is slightly different between Fuselages and Wings. Additional information about each section type is found in the Cross-Section Details subject.
Fuselage cross-sections may be rotated about the component X, Y, or Z axes around the center of the cross-section. The locations where feature lines pass through the cross-section may also be rotated along the section curve by using the Spin parameter. This tutorial demonstrates how to enter the desired cross-section rotation angle in degrees and how to use Spin effectively. Note that Skinning controls the feature line curves passing through the section and the skinning angles are defined in reference to that section. This means that by rotating a cross-section, you also effectively alter the physical direction of the feature line. Spin further affects this by altering the curve location where the feature lines are placed.