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Oscillating airfoil problem
Dear Friends,
I am working on an oscillating airfoil problem at present and I have a few doubts in this regards. I am trying to solve AGARD CT5 test case which is inviscid flow past harmonically oscillating NACA0012 airfoil. The variation of AOA is given as alpha(t) = alp_mean + alpha_o*sin(wt) where alp_mean = 0.016deg, alpha_o= 2.51 deg. Instead of w, what is reported commonly is the reduced frequency, k = w*chord/ 2*U_infty. For this case at hand, k = 0.0814. The NACA airfoil has a chord of unity and my freestream Mach is 0.755. Since I need my w for calculations, I need U_infty. I plan to calculate U_infty as U_infty = Mach * a_infty My question is what reference temperature must be used to calculate a_infty ? And what would be the corressponding w ? I calculated w as around 41 rad/s, but my results show reasonable disagreement with experiments, eventhough the 'hysterisis oval' I am supposed to get is seen in my computations. Can anyone in this field give me a reply, I have been stuck for nearly two weeks on this problem Thanks in advance, Ganesh |

Re: Oscillating airfoil problem
hi,
Actually, the temperature doesn't matter much as long as it is around experimental temperature condition (say 20 degree). you have no problem to calculate U-infty by using U_infty = Mach * a_infty. Once you have U_infty, you can easily work out w(Omiga). The most important issue is that you should define your k consistent with that in the experiment. Some studies use k = w*chord/ 2*U_infty and other use k = w*chord/U_infty. So check with the expemental document to make sure you have used the same difinition. |

Re: Oscillating airfoil problem
Dear Asue,
Thanks for your reply. I did use a temperature of around 25 C and calculated w. I have checked out k and its definition is consistent with the experiment. I think my code has a bug somewhere else, not possibly on this account. Thankyou for your suggestion. Regards, Ganesh |

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