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RG-12 (rg12-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG-12 (rg12-il)
Reynolds number: 100,000
Max Cl/Cd: 47.26 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12-il-100000-n5.txt
Download as CSV file: xf-rg12-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-12                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5193   0.09251   0.08740  -0.0260   1.0000   0.0214
  -9.500  -0.5302   0.08518   0.08017  -0.0301   1.0000   0.0205
  -9.250  -0.5398   0.07538   0.07041  -0.0370   1.0000   0.0194
  -9.000  -0.5516   0.06919   0.06423  -0.0414   1.0000   0.0192
  -8.750  -0.5692   0.06452   0.05953  -0.0431   1.0000   0.0192
  -8.500  -0.5841   0.06072   0.05568  -0.0428   1.0000   0.0190
  -8.250  -0.5950   0.05676   0.05159  -0.0422   1.0000   0.0189
  -8.000  -0.6029   0.05274   0.04738  -0.0412   1.0000   0.0188
  -7.750  -0.6078   0.04861   0.04298  -0.0399   1.0000   0.0188
  -7.500  -0.6082   0.04471   0.03873  -0.0383   1.0000   0.0187
  -7.250  -0.6046   0.04104   0.03468  -0.0365   1.0000   0.0188
  -7.000  -0.5975   0.03756   0.03075  -0.0347   1.0000   0.0189
  -6.750  -0.5862   0.03464   0.02731  -0.0329   1.0000   0.0194
  -6.500  -0.5744   0.03188   0.02428  -0.0315   1.0000   0.0206
  -6.250  -0.5582   0.03035   0.02256  -0.0302   1.0000   0.0222
  -6.000  -0.5406   0.02848   0.02040  -0.0288   1.0000   0.0237
  -5.750  -0.5216   0.02637   0.01793  -0.0273   1.0000   0.0245
  -5.500  -0.5016   0.02452   0.01579  -0.0259   1.0000   0.0254
  -5.250  -0.4811   0.02293   0.01396  -0.0244   1.0000   0.0267
  -5.000  -0.4605   0.02163   0.01245  -0.0230   1.0000   0.0282
  -4.750  -0.4414   0.02020   0.01094  -0.0217   1.0000   0.0307
  -4.500  -0.4210   0.01935   0.01004  -0.0205   1.0000   0.0361
  -4.250  -0.4007   0.01847   0.00912  -0.0194   1.0000   0.0446
  -4.000  -0.3800   0.01764   0.00829  -0.0183   1.0000   0.0589
  -3.750  -0.3591   0.01690   0.00766  -0.0173   1.0000   0.0852
  -3.500  -0.3379   0.01622   0.00712  -0.0165   1.0000   0.1197
  -3.250  -0.3169   0.01558   0.00671  -0.0157   1.0000   0.1719
  -3.000  -0.2863   0.01483   0.00635  -0.0170   0.9959   0.2698
  -2.750  -0.2542   0.01394   0.00612  -0.0186   0.9897   0.4229
  -2.500  -0.2259   0.01323   0.00633  -0.0183   0.9834   0.6263
  -2.250  -0.1975   0.01321   0.00650  -0.0176   0.9747   0.7404
  -2.000  -0.1663   0.01328   0.00653  -0.0176   0.9665   0.7943
  -1.750  -0.1348   0.01332   0.00648  -0.0177   0.9581   0.8329
  -1.500  -0.1050   0.01333   0.00643  -0.0174   0.9486   0.8630
  -1.250  -0.0699   0.01334   0.00636  -0.0182   0.9411   0.8893
  -1.000  -0.0339   0.01333   0.00625  -0.0192   0.9326   0.9127
  -0.750   0.0092   0.01332   0.00615  -0.0218   0.9258   0.9318
  -0.500   0.0569   0.01330   0.00604  -0.0255   0.9189   0.9478
  -0.250   0.1069   0.01325   0.00591  -0.0298   0.9116   0.9606
   0.000   0.1556   0.01315   0.00575  -0.0339   0.9030   0.9704
   0.250   0.2036   0.01303   0.00558  -0.0380   0.8918   0.9769
   0.500   0.2480   0.01289   0.00541  -0.0414   0.8788   0.9833
   0.750   0.2925   0.01273   0.00522  -0.0447   0.8642   0.9880
   1.000   0.3345   0.01258   0.00505  -0.0475   0.8475   0.9930
   1.250   0.3742   0.01245   0.00491  -0.0499   0.8278   0.9984
   1.500   0.4049   0.01237   0.00480  -0.0504   0.8063   1.0000
   1.750   0.4295   0.01234   0.00474  -0.0497   0.7828   1.0000
   2.000   0.4536   0.01234   0.00472  -0.0489   0.7590   1.0000
   2.250   0.4768   0.01238   0.00471  -0.0478   0.7344   1.0000
   2.500   0.4981   0.01245   0.00474  -0.0465   0.7086   1.0000
   2.750   0.5192   0.01256   0.00480  -0.0450   0.6822   1.0000
   3.000   0.5400   0.01271   0.00488  -0.0435   0.6553   1.0000
   3.250   0.5610   0.01288   0.00503  -0.0421   0.6275   1.0000
   3.500   0.5822   0.01309   0.00517  -0.0407   0.5987   1.0000
   3.750   0.6036   0.01334   0.00534  -0.0393   0.5689   1.0000
   4.000   0.6253   0.01361   0.00554  -0.0381   0.5381   1.0000
   4.250   0.6471   0.01392   0.00578  -0.0368   0.5057   1.0000
   4.500   0.6688   0.01426   0.00609  -0.0356   0.4725   1.0000
   4.750   0.6904   0.01464   0.00639  -0.0345   0.4381   1.0000
   5.000   0.7118   0.01506   0.00673  -0.0333   0.4019   1.0000
   5.250   0.7331   0.01553   0.00711  -0.0321   0.3644   1.0000
   5.500   0.7540   0.01605   0.00754  -0.0310   0.3266   1.0000
   5.750   0.7746   0.01663   0.00802  -0.0299   0.2879   1.0000
   6.000   0.7952   0.01726   0.00860  -0.0288   0.2488   1.0000
   6.250   0.8153   0.01797   0.00921  -0.0277   0.2100   1.0000
   6.500   0.8350   0.01877   0.00989  -0.0266   0.1726   1.0000
   6.750   0.8541   0.01968   0.01066  -0.0255   0.1385   1.0000
   7.000   0.8730   0.02064   0.01152  -0.0244   0.1088   1.0000
   7.250   0.8910   0.02172   0.01250  -0.0231   0.0853   1.0000
   7.500   0.9091   0.02280   0.01360  -0.0218   0.0673   1.0000
   7.750   0.9263   0.02398   0.01485  -0.0205   0.0534   1.0000
   8.000   0.9414   0.02538   0.01630  -0.0188   0.0455   1.0000
   8.250   0.9571   0.02673   0.01777  -0.0171   0.0395   1.0000
   8.500   0.9720   0.02819   0.01934  -0.0155   0.0340   1.0000
   8.750   0.9872   0.02962   0.02091  -0.0140   0.0298   1.0000
   9.000   0.9989   0.03156   0.02292  -0.0122   0.0272   1.0000
   9.250   1.0137   0.03347   0.02507  -0.0106   0.0248   1.0000
   9.500   1.0275   0.03506   0.02691  -0.0091   0.0218   1.0000
   9.750   1.0390   0.03691   0.02894  -0.0075   0.0201   1.0000
  10.000   1.0481   0.03910   0.03136  -0.0057   0.0191   1.0000
  10.250   1.0528   0.04194   0.03441  -0.0037   0.0182   1.0000
  10.500   1.0537   0.04517   0.03790  -0.0015   0.0177   1.0000
  10.750   1.0521   0.04794   0.04101   0.0009   0.0174   1.0000
  11.000   1.0457   0.05108   0.04449   0.0032   0.0172   1.0000
  11.250   1.0362   0.05441   0.04812   0.0048   0.0170   1.0000
  11.500   1.0235   0.05815   0.05215   0.0056   0.0168   1.0000
  11.750   1.0085   0.06240   0.05666   0.0053   0.0167   1.0000
  12.000   0.9923   0.06725   0.06175   0.0038   0.0167   1.0000
  12.250   0.9744   0.07293   0.06765   0.0011   0.0168   1.0000
  12.500   0.9554   0.07950   0.07440  -0.0029   0.0169   1.0000
  12.750   0.9363   0.08691   0.08196  -0.0078   0.0171   1.0000
  13.000   0.9172   0.09512   0.09029  -0.0134   0.0174   1.0000
  13.250   0.8952   0.10493   0.10021  -0.0200   0.0175   1.0000
  13.500   0.8772   0.11440   0.10972  -0.0259   0.0178   1.0000
  13.750   0.8527   0.12785   0.12321  -0.0339   0.0184   1.0000
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