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GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
Reynolds number: 100,000
Max Cl/Cd: 59.44 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe332-il-100000-n5.txt
Download as CSV file: xf-goe332-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 332 (PFALZ 61) AIRFOIL                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1637   0.10647   0.10158  -0.0603   0.9683   0.0611
  -8.750  -0.1557   0.10378   0.09890  -0.0662   0.9560   0.0645
  -8.500  -0.1554   0.10163   0.09677  -0.0746   0.9394   0.0652
  -8.250  -0.1313   0.09620   0.09134  -0.0751   0.9364   0.0661
  -8.000  -0.1119   0.09247   0.08759  -0.0756   0.9278   0.0674
  -7.750  -0.0928   0.08900   0.08409  -0.0785   0.9202   0.0691
  -7.500  -0.0785   0.08585   0.08091  -0.0815   0.9091   0.0710
  -7.250  -0.0656   0.08270   0.07773  -0.0858   0.8972   0.0736
  -6.750  -0.0308   0.07498   0.06991  -0.0992   0.8767   0.0779
  -6.500  -0.0121   0.07216   0.06705  -0.0994   0.8682   0.0800
  -6.250   0.0090   0.06898   0.06380  -0.1031   0.8597   0.0823
  -6.000   0.0286   0.06584   0.06056  -0.1078   0.8494   0.0850
  -5.500   0.0817   0.05405   0.04824  -0.1254   0.8310   0.0658
  -5.250   0.1038   0.05188   0.04603  -0.1260   0.8247   0.0671
  -4.750   0.1597   0.04182   0.03524  -0.1349   0.8089   0.0547
  -4.500   0.1828   0.03934   0.03259  -0.1361   0.8008   0.0540
  -4.250   0.2101   0.03650   0.02947  -0.1379   0.7939   0.0533
  -4.000   0.2376   0.03365   0.02628  -0.1394   0.7872   0.0527
  -3.750   0.2644   0.03099   0.02323  -0.1405   0.7798   0.0525
  -3.500   0.2952   0.02854   0.02026  -0.1418   0.7744   0.0537
  -3.250   0.3210   0.02674   0.01804  -0.1419   0.7666   0.0544
  -3.000   0.3498   0.02518   0.01608  -0.1423   0.7604   0.0545
  -2.750   0.3782   0.02391   0.01445  -0.1425   0.7543   0.0548
  -2.500   0.4049   0.02295   0.01319  -0.1423   0.7471   0.0553
  -2.250   0.4342   0.02200   0.01206  -0.1426   0.7416   0.0560
  -2.000   0.4596   0.02140   0.01139  -0.1422   0.7345   0.0572
  -1.750   0.4870   0.02094   0.01084  -0.1421   0.7281   0.0595
  -1.500   0.5153   0.02047   0.01025  -0.1421   0.7224   0.0623
  -1.250   0.5406   0.02007   0.00976  -0.1416   0.7150   0.0643
  -1.000   0.5690   0.01960   0.00922  -0.1415   0.7093   0.0663
  -0.750   0.5942   0.01934   0.00898  -0.1410   0.7023   0.0691
  -0.500   0.6211   0.01909   0.00869  -0.1407   0.6956   0.0733
  -0.250   0.6487   0.01887   0.00846  -0.1405   0.6896   0.0809
   0.000   0.6736   0.01877   0.00842  -0.1399   0.6820   0.0950
   0.250   0.7022   0.01856   0.00821  -0.1398   0.6761   0.1275
   0.500   0.7270   0.01853   0.00822  -0.1393   0.6685   0.1670
   0.750   0.7545   0.01831   0.00815  -0.1393   0.6620   0.2239
   1.000   0.7783   0.01662   0.00822  -0.1382   0.6558   1.0000
   1.250   0.8037   0.01681   0.00824  -0.1376   0.6486   1.0000
   1.500   0.8323   0.01693   0.00814  -0.1376   0.6430   1.0000
   1.750   0.8559   0.01718   0.00831  -0.1368   0.6351   1.0000
   2.000   0.8829   0.01734   0.00832  -0.1366   0.6287   1.0000
   2.250   0.9081   0.01756   0.00845  -0.1360   0.6217   1.0000
   2.500   0.9334   0.01777   0.00857  -0.1355   0.6144   1.0000
   2.750   0.9604   0.01794   0.00863  -0.1353   0.6082   1.0000
   3.000   0.9836   0.01821   0.00888  -0.1345   0.6000   1.0000
   3.250   1.0111   0.01836   0.00893  -0.1343   0.5938   1.0000
   3.500   1.0333   0.01866   0.00925  -0.1334   0.5853   1.0000
   3.750   1.0595   0.01885   0.00936  -0.1331   0.5784   1.0000
   4.000   1.0823   0.01914   0.00967  -0.1322   0.5701   1.0000
   4.250   1.1074   0.01935   0.00983  -0.1317   0.5626   1.0000
   4.500   1.1301   0.01964   0.01014  -0.1308   0.5543   1.0000
   4.750   1.1545   0.01988   0.01036  -0.1302   0.5465   1.0000
   5.000   1.1767   0.02019   0.01069  -0.1293   0.5379   1.0000
   5.250   1.2007   0.02042   0.01091  -0.1286   0.5299   1.0000
   5.500   1.2221   0.02077   0.01131  -0.1275   0.5210   1.0000
   5.750   1.2461   0.02101   0.01153  -0.1269   0.5133   1.0000
   6.000   1.2663   0.02140   0.01198  -0.1256   0.5039   1.0000
   6.500   1.3092   0.02208   0.01272  -0.1236   0.4866   1.0000
   6.750   1.3315   0.02240   0.01303  -0.1227   0.4785   1.0000
   7.000   1.3503   0.02280   0.01347  -0.1212   0.4683   1.0000
   7.250   1.3691   0.02321   0.01393  -0.1198   0.4583   1.0000
   7.500   1.3896   0.02355   0.01423  -0.1186   0.4491   1.0000
   7.750   1.4055   0.02408   0.01486  -0.1167   0.4390   1.0000
   8.000   1.4247   0.02454   0.01531  -0.1154   0.4309   1.0000
   8.250   1.4409   0.02508   0.01596  -0.1137   0.4220   1.0000
   8.500   1.4578   0.02561   0.01651  -0.1120   0.4140   1.0000
   8.750   1.4718   0.02619   0.01716  -0.1099   0.4054   1.0000
   9.000   1.4859   0.02680   0.01782  -0.1079   0.3969   1.0000
   9.250   1.4991   0.02743   0.01852  -0.1058   0.3881   1.0000
   9.500   1.5106   0.02818   0.01936  -0.1035   0.3793   1.0000
   9.750   1.5240   0.02887   0.02008  -0.1016   0.3713   1.0000
  10.000   1.5344   0.02974   0.02108  -0.0993   0.3632   1.0000
  10.250   1.5467   0.03053   0.02192  -0.0974   0.3556   1.0000
  10.500   1.5545   0.03155   0.02308  -0.0950   0.3469   1.0000
  10.750   1.5628   0.03249   0.02403  -0.0927   0.3374   1.0000
  11.000   1.5640   0.03386   0.02553  -0.0899   0.3260   1.0000
  11.250   1.5650   0.03533   0.02708  -0.0873   0.3141   1.0000
  11.500   1.5648   0.03697   0.02876  -0.0848   0.3017   1.0000
  11.750   1.5637   0.03879   0.03062  -0.0824   0.2893   1.0000
  12.000   1.5622   0.04084   0.03278  -0.0804   0.2773   1.0000
  12.250   1.5610   0.04301   0.03506  -0.0786   0.2657   1.0000
  12.500   1.5592   0.04532   0.03746  -0.0770   0.2543   1.0000
  12.750   1.5561   0.04784   0.04004  -0.0754   0.2427   1.0000
  13.000   1.5510   0.05066   0.04291  -0.0740   0.2302   1.0000
  13.250   1.5447   0.05375   0.04607  -0.0728   0.2170   1.0000
  13.500   1.5376   0.05707   0.04944  -0.0718   0.2039   1.0000
  13.750   1.5300   0.06057   0.05301  -0.0710   0.1914   1.0000
  14.000   1.5216   0.06431   0.05679  -0.0704   0.1796   1.0000
  14.250   1.5112   0.06840   0.06091  -0.0700   0.1678   1.0000
  14.500   1.4992   0.07285   0.06539  -0.0697   0.1555   1.0000
  14.750   1.4867   0.07755   0.07013  -0.0698   0.1431   1.0000
  15.000   1.4746   0.08234   0.07499  -0.0700   0.1305   1.0000
  15.250   1.4604   0.08755   0.08024  -0.0705   0.1159   1.0000
  15.500   1.4426   0.09344   0.08611  -0.0714   0.1014   1.0000
  15.750   1.4243   0.09956   0.09220  -0.0725   0.0902   1.0000
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