XFLR5 Part5 Piper PA-28 Cherokee Wing Analysis
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- Опубликовано: 20 авг 2024
- XFLR5 Hands on Tutorial Series
PART5 Piper PA-28 Cheorkee Wing Analysis
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Tapered Cherokee Wing Examples:
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NACA 65(2)-415 Airfoil:
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Thank you for the video
You are welcome thanks for the feedback.
Hello sir, can you do stability analysis on this particular aircraft? and my 3d model is not showing on the on the 3d view? what should I do sir?
I would like to pay you to run some analysis on adding some long range fuel tanks to my PA28-181- is this possible? If so I will give you my email address as long s you can delete it fairly quickly! The analysis would be to prove the wing can deal with the extra loading. I would add the fuel outboard of the main tanks like the Piper PA28-236 - this model has stronger brackets at the wind root. However I would have an overall lighter aircraft and I would always fly within weight and balance (ie when taking long range fuel I would not take passengers)
Whenever i plot a airfoil with chord of 100 mm , i get Cl values of 100s , can you help out with this problem?
Well Abhijeet normally you use the dimensions in normalized form like it goes from 0 to 1 ok. No wonder if you use the chord length of 100mm accordingly you will be getting higher Cl values. Use the co-ordinates in normalized form everything should be ok then, thanks.
Hello im making active spoiler and in xflr5 with flap extended at 30 deg in plane simulation program is not ploting anything.
Do you know maybe why is that?
Im getting grahs for 20 and 10 deg.
Hi Jan, well there could be several reasons. Either its convergence problem or Reynolds number out of flight envelope, solver issue etc.
May be try your simulation first with 25 deg or less and then increase flap angle slowly to reach 30deg.
Could also be an issue with number of panels distribution at 30 degrees test case.
@@Simulation-Engineer Error looks like this """Span pos = 0.00 , Re = 358447 , A+Ai+Twist = 58.5 could not be interpolated"""" I did direct analysis for that reynolds number and it didnt help. I got results only for attack angle ranging from 12 to 18 but not for 0-12 and 18-20.
Well that means there is a problem at the wing root position. Try the following:
- perform direct analysis using batch option to have finer resolution of Reynolds number around the mentioned Reynolds number
- also try to change the panel distribution at the wing root
- may be use of other vortex lattice method or panel method could help too
-may be start from -2 deg/-1 deg in 3D analysis to get the desired angle of attack
- make sure in direct analysis that if the airfoil is stalled or not
Good luck
@@Simulation-Engineer I performed batch analysis, changed panels, used different methods and i know wing is not stalled for given AoA.Im getting now little longer graphs but still no full characteristics. If flap is set for 0 deg i have full graph but the more i increse the deflection of flap (increase angle) the shorter the graph gets. Do you know why this might be?
Well normally increasing the flap angle results in increased camber. That's why these preliminary tools are not so optimized for high life devices setup.
I would recommend the following:
- Use panel method with viscous option on
- another important point make sure that you use an airfoil with flapped geometry in 2d airfoil analysis then select it in your wing definition.
Good luck ☺
Respected sir, I am doing major project on prandtl D wing with xflr5 software but I don't have knowledge about this software but I know some CFD software like (Ansys) can you help me to find stability if possible please share your email id sir thank you...
Thanks for the comment Suraj, well I would recommend reading aerodynamic stability literature including stability & control derivatives. I will see if I can perform a XFLR5 stability tutorial in the near future.