ONERA M6 Wing Validation

JAMES_SPIR · May 27, 2024, 09:46

Hi,
I am trying to reproduce the ONERA M6 wing simulation in this video (https://www.youtube.com/watch?v=wnAbyAZHcGo&t=1719s), however I use ANSYS version R19.2 instead of the 2021 R1 used in the YouTube video. Although I follow every step as shown in the video, my Lift Coefficient value is 30% less than the expected. Both Pressure and Drag Coefficient are the ones expected. The simulation converged. Any ideas what could be wrong? I have done it quite a few times with the same results.

BadOwl · February 23, 2025, 04:58

Ok, so perhaps you've already found an explanation, in which case i'm really interested in hearing from you because i'm having the same exact issue (on openfoam but the same issue nonetheless)

If you havent found an explanation yet, i might have an explanation of my own, which i'd like to confront to youre experience because it's really (like REALLY) fishy and i dont understand why.

If you look closely, on the nasa reference page where the guy making your tutorial video found the geometry, NASA wrote they used a reference area of 1.1531508411923
I guess you uesed this reference area, just like i did.

(They did not specify units, but i'm assuming it's metric (because if it was imperial, the resulting metric reference area would be completely absurd)

HOWEVER, if you look closely at 22:34 in the tutorial video, where the guy pulls up a calculation sheed, he indicates using a reference area of 0.76532m². I have absolutely no idea why there is such a discrepancy between the reference areas but when i use the 0.76532 m², all my coefficients (drag and lift) converge towards values much closer to what is expected from the litterature.

TLDR : Are you absolutely sure your reference values are coherent with the data you are ereferencing? becasuse it seems that for the onera M6, there is some (or even a lot) of variation between studies. (check this especially if all other flow parameters are coherent (such as pressure coefficients and shock location are correct)

May 27, 2024, 09:46	ONERA M6 Wing Validation	#1
JAMES_SPIR New Member Spiridakos Dimitrios Join Date: Oct 2015 Location: Athens, Greece Posts: 2 Rep Power: 0	Hi, I am trying to reproduce the ONERA M6 wing simulation in this video (https://www.youtube.com/watch?v=wnAbyAZHcGo&t=1719s), however I use ANSYS version R19.2 instead of the 2021 R1 used in the YouTube video. Although I follow every step as shown in the video, my Lift Coefficient value is 30% less than the expected. Both Pressure and Drag Coefficient are the ones expected. The simulation converged. Any ideas what could be wrong? I have done it quite a few times with the same results.

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February 23, 2025, 04:58		#2
BadOwl New Member Join Date: Jan 2025 Posts: 11 Rep Power: 2	Ok, so perhaps you've already found an explanation, in which case i'm really interested in hearing from you because i'm having the same exact issue (on openfoam but the same issue nonetheless) If you havent found an explanation yet, i might have an explanation of my own, which i'd like to confront to youre experience because it's really (like REALLY) fishy and i dont understand why. If you look closely, on the nasa reference page where the guy making your tutorial video found the geometry, NASA wrote they used a reference area of 1.1531508411923 I guess you uesed this reference area, just like i did. (They did not specify units, but i'm assuming it's metric (because if it was imperial, the resulting metric reference area would be completely absurd) HOWEVER, if you look closely at 22:34 in the tutorial video, where the guy pulls up a calculation sheed, he indicates using a reference area of 0.76532m². I have absolutely no idea why there is such a discrepancy between the reference areas but when i use the 0.76532 m², all my coefficients (drag and lift) converge towards values much closer to what is expected from the litterature. TLDR : Are you absolutely sure your reference values are coherent with the data you are ereferencing? becasuse it seems that for the onera M6, there is some (or even a lot) of variation between studies. (check this especially if all other flow parameters are coherent (such as pressure coefficients and shock location are correct)