Timeline for What is the amount of lift produced by friction?
Current License: CC BY-SA 4.0
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| when toggle format | what | by | license | comment | |
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| Apr 21, 2020 at 22:47 | history | edited | Peter Kämpf | CC BY-SA 4.0 |
added 64 characters in body
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| Apr 21, 2020 at 22:45 | comment | added | Peter Kämpf | @m2as3registeredservicesohmone: You are right. In XFOIL.f, subroutine CLCALC, the lift coefficient is summed up in the line CL = CL + DX* AG (plop over N panels). No additional summand using DY, so tangential forces are neglected. Since they are two magnitudes lower than pressure, this makes sense. | |
| Apr 21, 2020 at 3:13 | comment | added | user46017 | From web.mit.edu/aeroutil_v1.0/xfoil_doc.txt; The lift and moment coefficients CL, CM, are calculated by direct surface pressure integration: / _ / CL = L/q = | Cp dx CM = M/q = | -Cp [(x-xref) dx + (y-yref) dy] / / _ where x = x cos(a) + y sin(a) ; a = angle of attack _ y = y cos(a) - x sin(a) | |
| Apr 17, 2020 at 19:09 | comment | added | JZYL | When airfoil is at a non-zero AOA, more shear forces will translate into lift component. Doesn't xfoil compute far-field lift and drag instead of surface integration? | |
| Apr 17, 2020 at 17:58 | history | answered | Peter Kämpf | CC BY-SA 4.0 |