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SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 200,000
Max Cl/Cd: 77.26 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd2030-il-200000.txt
Download as CSV file: xf-sd2030-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2030-086-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4528   0.09106   0.08761  -0.0395   1.0000   0.0475
  -8.500  -0.4665   0.08802   0.08465  -0.0406   1.0000   0.0476
  -8.250  -0.4824   0.08497   0.08164  -0.0414   1.0000   0.0477
  -8.000  -0.4932   0.08171   0.07836  -0.0417   1.0000   0.0477
  -7.750  -0.5032   0.07865   0.07525  -0.0412   1.0000   0.0478
  -7.500  -0.5128   0.07253   0.06924  -0.0394   1.0000   0.0489
  -7.250  -0.5121   0.07020   0.06696  -0.0366   1.0000   0.0497
  -7.000  -0.5128   0.06796   0.06474  -0.0345   1.0000   0.0506
  -6.750  -0.5142   0.06541   0.06217  -0.0330   1.0000   0.0516
  -6.500  -0.5148   0.06257   0.05928  -0.0321   1.0000   0.0532
  -6.250  -0.5136   0.05939   0.05602  -0.0316   1.0000   0.0554
  -6.000  -0.5095   0.05706   0.05297  -0.0331   1.0000   0.0606
  -5.750  -0.5076   0.05031   0.04637  -0.0327   1.0000   0.0625
  -5.500  -0.4977   0.04813   0.04424  -0.0312   1.0000   0.0643
  -5.250  -0.4862   0.04571   0.04172  -0.0303   1.0000   0.0667
  -5.000  -0.4594   0.04122   0.03657  -0.0333   0.9973   0.0757
  -4.750  -0.4311   0.03821   0.03359  -0.0352   0.9947   0.0784
  -4.500  -0.4001   0.03539   0.03027  -0.0374   0.9907   0.0898
  -4.250  -0.3640   0.02569   0.01932  -0.0365   0.9897   0.0426
  -4.000  -0.3308   0.02312   0.01624  -0.0374   0.9871   0.0416
  -3.750  -0.2956   0.02133   0.01406  -0.0387   0.9847   0.0419
  -3.500  -0.2621   0.01973   0.01215  -0.0395   0.9820   0.0414
  -3.250  -0.2308   0.01856   0.01082  -0.0400   0.9781   0.0420
  -3.000  -0.1968   0.01764   0.00981  -0.0411   0.9747   0.0440
  -2.750  -0.1599   0.01700   0.00908  -0.0429   0.9718   0.0472
  -2.500  -0.1302   0.01619   0.00832  -0.0436   0.9673   0.0540
  -2.250  -0.0980   0.01550   0.00766  -0.0445   0.9626   0.0678
  -2.000  -0.0638   0.01418   0.00713  -0.0464   0.9594   0.2351
  -1.750  -0.0381   0.01271   0.00724  -0.0467   0.9558   0.6156
  -1.500  -0.0253   0.01224   0.00761  -0.0420   0.9489   0.8745
  -1.250   0.0514   0.01233   0.00763  -0.0510   0.9519   0.9901
  -1.000   0.0964   0.01238   0.00752  -0.0548   0.9481   1.0000
  -0.750   0.1394   0.01241   0.00741  -0.0580   0.9444   1.0000
  -0.500   0.1674   0.01238   0.00728  -0.0582   0.9362   1.0000
  -0.250   0.2103   0.01232   0.00712  -0.0613   0.9317   1.0000
   0.000   0.2471   0.01225   0.00699  -0.0631   0.9256   1.0000
   0.250   0.2857   0.01211   0.00679  -0.0652   0.9191   1.0000
   0.500   0.3380   0.01186   0.00651  -0.0699   0.9162   1.0000
   0.750   0.3679   0.01169   0.00632  -0.0701   0.9070   1.0000
   1.000   0.4144   0.01131   0.00594  -0.0734   0.9025   1.0000
   1.250   0.4426   0.01110   0.00572  -0.0732   0.8928   1.0000
   1.500   0.4854   0.01068   0.00530  -0.0756   0.8872   1.0000
   1.750   0.5105   0.01047   0.00511  -0.0746   0.8756   1.0000
   2.000   0.5377   0.01025   0.00490  -0.0739   0.8641   1.0000
   2.250   0.5656   0.01003   0.00469  -0.0733   0.8520   1.0000
   2.500   0.5925   0.00984   0.00451  -0.0726   0.8383   1.0000
   2.750   0.6183   0.00970   0.00439  -0.0716   0.8226   1.0000
   3.000   0.6441   0.00957   0.00426  -0.0706   0.8045   1.0000
   3.250   0.6682   0.00951   0.00418  -0.0693   0.7828   1.0000
   3.500   0.6923   0.00947   0.00411  -0.0680   0.7565   1.0000
   3.750   0.7150   0.00950   0.00411  -0.0665   0.7243   1.0000
   4.000   0.7375   0.00959   0.00410  -0.0650   0.6831   1.0000
   4.250   0.7587   0.00982   0.00413  -0.0632   0.6302   1.0000
   4.500   0.7773   0.01024   0.00426  -0.0610   0.5647   1.0000
   4.750   0.7937   0.01083   0.00452  -0.0587   0.4941   1.0000
   5.000   0.8096   0.01150   0.00486  -0.0564   0.4264   1.0000
   5.250   0.8260   0.01221   0.00527  -0.0544   0.3640   1.0000
   5.500   0.8432   0.01292   0.00571  -0.0526   0.3081   1.0000
   5.750   0.8610   0.01365   0.00619  -0.0510   0.2592   1.0000
   6.000   0.8793   0.01440   0.00674  -0.0495   0.2158   1.0000
   6.250   0.8982   0.01514   0.00733  -0.0481   0.1787   1.0000
   6.500   0.9166   0.01597   0.00798  -0.0467   0.1485   1.0000
   6.750   0.9356   0.01678   0.00871  -0.0453   0.1250   1.0000
   7.000   0.9543   0.01765   0.00949  -0.0439   0.1083   1.0000
   7.250   0.9734   0.01854   0.01039  -0.0425   0.0957   1.0000
   7.500   0.9926   0.01945   0.01132  -0.0412   0.0854   1.0000
   7.750   1.0112   0.02058   0.01241  -0.0398   0.0773   1.0000
   8.000   1.0313   0.02129   0.01318  -0.0387   0.0689   1.0000
   8.250   1.0506   0.02214   0.01412  -0.0375   0.0605   1.0000
   8.500   1.0682   0.02326   0.01527  -0.0362   0.0529   1.0000
   8.750   1.0865   0.02394   0.01605  -0.0348   0.0455   1.0000
   9.000   1.1028   0.02522   0.01745  -0.0332   0.0377   1.0000
   9.250   1.1178   0.02738   0.01961  -0.0316   0.0324   1.0000
   9.500   1.1354   0.02883   0.02129  -0.0300   0.0287   1.0000
   9.750   1.1511   0.03023   0.02279  -0.0285   0.0263   1.0000
  10.000   1.1645   0.03308   0.02581  -0.0270   0.0238   1.0000
  10.250   1.1773   0.03465   0.02770  -0.0250   0.0223   1.0000
  10.500   1.1878   0.03708   0.03044  -0.0229   0.0215   1.0000
  10.750   1.1934   0.03959   0.03326  -0.0203   0.0208   1.0000
  11.000   1.1947   0.04219   0.03615  -0.0173   0.0204   1.0000
  11.250   1.1914   0.04500   0.03926  -0.0141   0.0201   1.0000
  11.500   1.1840   0.04798   0.04253  -0.0110   0.0199   1.0000
  11.750   1.1729   0.05121   0.04604  -0.0081   0.0197   1.0000
  12.000   1.1529   0.05547   0.05066  -0.0056   0.0200   1.0000
  12.250   1.1315   0.06001   0.05550  -0.0042   0.0202   1.0000
  12.500   1.1082   0.06514   0.06090  -0.0042   0.0204   1.0000
  12.750   1.0817   0.07134   0.06736  -0.0057   0.0206   1.0000
  13.000   1.0545   0.07858   0.07483  -0.0092   0.0209   1.0000
  13.250   1.0269   0.08717   0.08362  -0.0147   0.0212   1.0000
  13.500   0.9959   0.09832   0.09493  -0.0227   0.0218   1.0000
  13.750   0.9601   0.11299   0.10969  -0.0329   0.0226   1.0000
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