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GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
Reynolds number: 100,000
Max Cl/Cd: 52.17 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe332-il-100000.txt
Download as CSV file: xf-goe332-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2994   0.13158   0.12706  -0.0359   1.0000   0.0722
  -9.500  -0.3241   0.13271   0.12832  -0.0326   1.0000   0.0723
  -9.250  -0.3481   0.13362   0.12935  -0.0297   1.0000   0.0724
  -9.000  -0.3110   0.12423   0.11992  -0.0266   0.9999   0.0741
  -8.750  -0.2863   0.11967   0.11532  -0.0303   0.9958   0.0764
  -8.500  -0.2660   0.11580   0.11144  -0.0352   0.9905   0.0792
  -8.250  -0.2497   0.11267   0.10829  -0.0423   0.9842   0.0827
  -8.000  -0.2539   0.11250   0.10815  -0.0528   0.9703   0.0842
  -7.750  -0.2328   0.10642   0.10206  -0.0543   0.9651   0.0854
  -7.500  -0.1980   0.10100   0.09659  -0.0551   0.9629   0.0887
  -7.250  -0.1824   0.09786   0.09344  -0.0585   0.9544   0.0920
  -7.000  -0.1693   0.09519   0.09076  -0.0666   0.9432   0.0962
  -6.750  -0.1467   0.09105   0.08656  -0.0819   0.9326   0.0984
  -6.500  -0.1355   0.08723   0.08278  -0.0771   0.9252   0.0998
  -6.250  -0.1094   0.08340   0.07891  -0.0788   0.9207   0.1029
  -6.000  -0.0912   0.08042   0.07590  -0.0826   0.9121   0.1071
  -5.750  -0.0562   0.07605   0.07135  -0.0987   0.9040   0.1136
  -5.250  -0.0189   0.06990   0.06522  -0.0978   0.8911   0.1207
  -5.000   0.0304   0.06509   0.06015  -0.1123   0.8873   0.1295
  -4.750   0.0348   0.06312   0.05823  -0.1091   0.8767   0.1314
  -4.500   0.0718   0.05972   0.05474  -0.1136   0.8733   0.1385
  -4.250   0.0955   0.05709   0.05190  -0.1186   0.8639   0.1460
  -4.000   0.1233   0.05421   0.04903  -0.1198   0.8592   0.1513
  -3.750   0.1662   0.05072   0.04534  -0.1261   0.8560   0.1641
  -3.500   0.1853   0.04957   0.04396  -0.1277   0.8456   0.1772
  -3.250   0.2162   0.04658   0.04100  -0.1290   0.8417   0.1836
  -3.000   0.2587   0.04367   0.03792  -0.1335   0.8387   0.1995
  -2.750   0.2702   0.04276   0.03691  -0.1323   0.8280   0.2129
  -2.500   0.3074   0.04042   0.03447  -0.1350   0.8241   0.2330
  -2.250   0.3266   0.03942   0.03339  -0.1347   0.8160   0.2619
  -2.000   0.3912   0.03472   0.02753  -0.1416   0.8108   0.1487
  -1.750   0.4418   0.03091   0.02276  -0.1444   0.8073   0.1090
  -1.500   0.4661   0.02988   0.02148  -0.1439   0.7995   0.1065
  -1.250   0.4988   0.02860   0.01988  -0.1444   0.7932   0.1053
  -1.000   0.5393   0.02727   0.01824  -0.1459   0.7892   0.1082
  -0.750   0.5570   0.02730   0.01809  -0.1441   0.7794   0.1116
  -0.500   0.5928   0.02614   0.01685  -0.1450   0.7742   0.1162
  -0.250   0.6173   0.02586   0.01655  -0.1442   0.7664   0.1224
   0.000   0.6462   0.02529   0.01598  -0.1440   0.7594   0.1336
   0.250   0.6833   0.02426   0.01499  -0.1448   0.7551   0.1634
   0.500   0.6988   0.02397   0.01504  -0.1429   0.7450   0.2371
   0.750   0.7311   0.02169   0.01450  -0.1426   0.7402   1.0000
   1.000   0.7509   0.02225   0.01483  -0.1411   0.7311   1.0000
   1.250   0.7828   0.02219   0.01454  -0.1413   0.7248   1.0000
   1.500   0.8061   0.02257   0.01478  -0.1404   0.7166   1.0000
   1.750   0.8346   0.02266   0.01472  -0.1402   0.7093   1.0000
   2.000   0.8625   0.02281   0.01474  -0.1400   0.7024   1.0000
   2.250   0.8867   0.02309   0.01493  -0.1392   0.6938   1.0000
   2.500   0.9210   0.02293   0.01462  -0.1398   0.6883   1.0000
   2.750   0.9393   0.02348   0.01516  -0.1382   0.6780   1.0000
   3.000   0.9763   0.02318   0.01470  -0.1392   0.6730   1.0000
   3.250   0.9918   0.02387   0.01543  -0.1373   0.6620   1.0000
   3.500   1.0289   0.02357   0.01498  -0.1383   0.6568   1.0000
   3.750   1.0445   0.02423   0.01569  -0.1363   0.6456   1.0000
   4.000   1.0812   0.02397   0.01531  -0.1373   0.6401   1.0000
   4.250   1.0966   0.02466   0.01606  -0.1354   0.6289   1.0000
   4.500   1.1280   0.02464   0.01597  -0.1356   0.6220   1.0000
   4.750   1.1487   0.02506   0.01643  -0.1344   0.6119   1.0000
   5.000   1.1751   0.02530   0.01664  -0.1340   0.6037   1.0000
   5.250   1.2001   0.02555   0.01689  -0.1334   0.5948   1.0000
   5.500   1.2225   0.02597   0.01735  -0.1324   0.5857   1.0000
   5.750   1.2514   0.02603   0.01738  -0.1324   0.5776   1.0000
   6.000   1.2699   0.02663   0.01805  -0.1309   0.5679   1.0000
   6.250   1.3020   0.02655   0.01794  -0.1313   0.5604   1.0000
   6.500   1.3176   0.02722   0.01870  -0.1294   0.5500   1.0000
   6.750   1.3546   0.02685   0.01823  -0.1304   0.5429   1.0000
   7.000   1.3671   0.02753   0.01904  -0.1280   0.5316   1.0000
   7.250   1.3930   0.02768   0.01922  -0.1275   0.5231   1.0000
   7.500   1.4160   0.02795   0.01953  -0.1266   0.5140   1.0000
   7.750   1.4355   0.02849   0.02015  -0.1253   0.5053   1.0000
   8.000   1.4627   0.02863   0.02033  -0.1251   0.4972   1.0000
   8.250   1.4784   0.02932   0.02113  -0.1233   0.4880   1.0000
   8.500   1.5117   0.02916   0.02091  -0.1239   0.4799   1.0000
   8.750   1.5214   0.03001   0.02194  -0.1211   0.4699   1.0000
   9.000   1.5508   0.03006   0.02199  -0.1212   0.4614   1.0000
   9.250   1.5650   0.03067   0.02273  -0.1191   0.4516   1.0000
   9.500   1.5835   0.03117   0.02330  -0.1176   0.4422   1.0000
   9.750   1.6163   0.03098   0.02304  -0.1181   0.4319   1.0000
  10.000   1.6196   0.03179   0.02405  -0.1143   0.4207   1.0000
  10.250   1.6323   0.03210   0.02440  -0.1118   0.4084   1.0000
  10.500   1.6454   0.03224   0.02454  -0.1093   0.3951   1.0000
  10.750   1.6579   0.03245   0.02472  -0.1067   0.3820   1.0000
  11.000   1.6646   0.03291   0.02523  -0.1034   0.3703   1.0000
  11.250   1.6606   0.03389   0.02636  -0.0987   0.3598   1.0000
  11.500   1.6656   0.03460   0.02712  -0.0955   0.3488   1.0000
  11.750   1.6743   0.03520   0.02770  -0.0929   0.3375   1.0000
  12.000   1.6641   0.03674   0.02945  -0.0884   0.3272   1.0000
  12.250   1.6619   0.03802   0.03083  -0.0850   0.3164   1.0000
  12.500   1.6637   0.03918   0.03201  -0.0823   0.3054   1.0000
  12.750   1.6539   0.04128   0.03432  -0.0790   0.2950   1.0000
  13.000   1.6468   0.04336   0.03653  -0.0763   0.2840   1.0000
  13.250   1.6399   0.04556   0.03880  -0.0739   0.2725   1.0000
  13.500   1.6310   0.04809   0.04141  -0.0718   0.2606   1.0000
  13.750   1.6166   0.05146   0.04492  -0.0700   0.2477   1.0000
  14.000   1.6022   0.05507   0.04864  -0.0685   0.2338   1.0000
  14.250   1.5873   0.05904   0.05269  -0.0674   0.2193   1.0000
  14.500   1.5707   0.06350   0.05719  -0.0667   0.2038   1.0000
  14.750   1.5515   0.06852   0.06220  -0.0663   0.1871   1.0000
  15.000   1.5303   0.07413   0.06783  -0.0663   0.1690   1.0000
  15.250   1.5071   0.08026   0.07392  -0.0666   0.1509   1.0000
  15.500   1.4823   0.08687   0.08048  -0.0673   0.1331   1.0000
  15.750   1.4575   0.09377   0.08733  -0.0684   0.1152   1.0000
  16.000   1.4336   0.10070   0.09415  -0.0697   0.1018   1.0000
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