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this geometry had a blunt trailing edge. and was solved with a blunt trailing edge. It was never made sharp.

Użyj kórła Solid Edge (model) ---> Femap ---> Ansys (destruction) Będziesz kórła Pan zadowolny

He used the reference length. In this case that should be the MAC.

@@johnwighton thank you!

@@레샹-n6p i THINK HE SETS THE REF LENGTH AS THE ROOT CHORD. iTS AN UNUSUAL LAYOUT, SO NOT EASY TO UNDERSTAND. Opps sorry about caps.

If possible you would want to use the CCS file format and then apply the "subsurface" parameter to create the control surface. If you have any more questions feel free to reach out to support@researchinflight.com

You can get the software by reaching out to us directly. This is not an open source software. We offer reduced rates for students and start ups. Please email daniel.enriquez@researchinflight.com

When using a half model with symmetry boundary condition, no beta angles are allowed. To change beta we would need to mirror the mesh and create a full AC model

Yes! Look in the Help documentation included with FlightStream and look for "Mesh_U" or "Mesh_V" paremeters. This should be just one line you have to add to the CCS file to specify U and V

@@AltairFlightStream Thanks! In the docs, it says you can specify the "growth rate" and gives the options: One of the following: 1=Uniform spacing; 2=Successive; 3=Dual-sided successive; 4=Reverse Successive. What do these do exactly?

@@comp_sci_aero8099 these options allow you to cluster the grid points. By setting the growth rate you can push more nodes near the start or end of the cross sections. In this application, successive clusters the nodes near top trailing edge, dual-sided pushes nodes near both the top/bottom trailing edges, and reverse successive pushes nodes to the bottom TE. For mesh sensitivity studies we recommend setting the spacing to uniform.

Unfortunately, currently FlightStream does not have the capability to calculate the frequencies associated with these dynamic stability modes. However, you can use the Stability & Control toolbox to calculate the dynamic derivatives and then use these values in a separate analysis. For example see here, www.aircraftflightmechanics.com/Dynamics/CherokeeExample.html

I'll add it to our future videos list. However, if you have an STL file you can use CAD Cross Sections tool to generate cross sections for use in a CCS file. Similar to this video. ruclips.net/video/zv_BNPGu5-c/видео.htmlfeature=shared

For dynamic stability analysis take a look at this video and see if it helps, ruclips.net/video/pR742r47Fw8/видео.html

Currently there is not a way to vary actuator disc thrust with velocity. However, we would suggest writing script files to batch run your analysis at different flight speeds and change the CT setting for each case accordingly. Remember to use unsteady analysis to calculate your propeller map ahead of time. Alternatively, you can choose to run an unsteady propeller analysis with your full aircraft geometry and this will capture the velocity dependent effects. Let me know if you have more questions!