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Wing aspect ratio value seems not correct #827
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I just checked, if I change "x-z-plane" by "x-y-plane" for the symmetry of wing 1, it gives the correct value, so it seems that "get_aspect_ratio()" did not use the correct reference area projection to calculate the AR. |
Hi @aidanjungo . Thanks for pointing this out. I'll have a look, why this has changed. Which TiGL version have you been using before (which didn't have this bug)? |
I am not sure of which version I was using because I installed cpacscreator via Conda. But now, I feel that Tigl3 has been update but maybe not cpacscreator, is it correct? |
Indeed, we have not updated cpacs creator yet. It still uses tigl 3.0.0 as a basis. |
I also made the code more const correct Addresses #827
I can reproduce this error. The error actually already existed in tigl 3.0.0. The reason for the error is, that the wing reference area is computed incorrectly, because wrong projection planes are passed to the reference area computation. |
This test demonstrates the problem: |
Apparently, Malo fixed the bug back then in the cpacs creator. I'll backport the fix into tigl. |
I backported the code from cpacs creator, which already solved the problem. Fixes #827
Added copyright header to winghelpers. Closes #827
I also made the code more const correct Addresses #827
I backported the code from cpacs creator, which already solved the problem. Fixes #827
Added copyright header to winghelpers. Closes #827
I also added unit tests for the TiglWingHelperFunctions. Addresses #827
I also made the code more const correct Addresses #827
I backported the code from cpacs creator, which already solved the problem. Fixes #827
Added copyright header to winghelpers. Closes #827
I also added unit tests for the TiglWingHelperFunctions. Addresses #827
tigl/src/wing/CCPACSWing.cpp
Lines 661 to 667 in 59ae251
I am not sure I completely understand how the formula to calculate AR has been changed recently, but when I use 'get_aspect_ratio()' for wing 1 of the D150 i got 526.71 before this change the value was 9.4.
It seems to me that it use the wrong reference area for the wing in the AR formula
If we use:
AR = (Span**2)/4 / RefArea *2
Before I think it was:
But now it seems to be:
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