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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 500,000
Max Cl/Cd: 109.07 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe195-il-500000-n5.txt
Download as CSV file: xf-goe195-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 195 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3527   0.10983   0.10738  -0.0309   1.0000   0.0129
 -10.000  -0.3500   0.10635   0.10392  -0.0320   1.0000   0.0134
  -9.750  -0.3598   0.09989   0.09748  -0.0344   1.0000   0.0145
  -9.500  -0.3543   0.09804   0.09565  -0.0343   1.0000   0.0147
  -9.250  -0.3505   0.09606   0.09370  -0.0341   1.0000   0.0148
  -9.000  -0.3486   0.09391   0.09157  -0.0339   0.9999   0.0150
  -8.750  -0.3354   0.09041   0.08807  -0.0373   0.9971   0.0154
  -8.500  -0.3224   0.08646   0.08411  -0.0415   0.9940   0.0159
  -8.250  -0.3115   0.08202   0.07968  -0.0460   0.9890   0.0165
  -8.000  -0.3098   0.07158   0.06924  -0.0576   0.9793   0.0181
  -7.750  -0.2880   0.06839   0.06603  -0.0629   0.9747   0.0184
  -7.500  -0.2682   0.06525   0.06288  -0.0676   0.9676   0.0187
  -7.250  -0.2237   0.02901   0.02582  -0.1222   0.9520   0.0215
  -7.000  -0.1895   0.02368   0.01968  -0.1293   0.9468   0.0222
  -6.750  -0.1632   0.02119   0.01693  -0.1312   0.9399   0.0228
  -6.500  -0.1345   0.02008   0.01570  -0.1322   0.9342   0.0233
  -6.250  -0.1070   0.01902   0.01449  -0.1329   0.9272   0.0236
  -6.000  -0.0788   0.01789   0.01318  -0.1335   0.9197   0.0240
  -5.750  -0.0508   0.01683   0.01192  -0.1340   0.9120   0.0244
  -5.500  -0.0227   0.01585   0.01075  -0.1343   0.9038   0.0248
  -5.250   0.0053   0.01502   0.00973  -0.1345   0.8945   0.0253
  -5.000   0.0332   0.01435   0.00889  -0.1346   0.8832   0.0259
  -4.750   0.0610   0.01368   0.00803  -0.1346   0.8695   0.0263
  -4.500   0.0888   0.01307   0.00726  -0.1345   0.8555   0.0267
  -4.250   0.1164   0.01256   0.00659  -0.1344   0.8398   0.0269
  -4.000   0.1440   0.01213   0.00601  -0.1342   0.8224   0.0272
  -3.750   0.1716   0.01176   0.00550  -0.1340   0.8058   0.0274
  -3.500   0.1991   0.01145   0.00505  -0.1338   0.7893   0.0276
  -3.250   0.2266   0.01118   0.00465  -0.1336   0.7735   0.0278
  -3.000   0.2542   0.01062   0.00398  -0.1336   0.7594   0.0283
  -2.750   0.2819   0.01024   0.00353  -0.1335   0.7471   0.0290
  -2.500   0.3098   0.01000   0.00321  -0.1334   0.7354   0.0296
  -2.250   0.3378   0.00979   0.00294  -0.1334   0.7240   0.0300
  -2.000   0.3658   0.00963   0.00271  -0.1333   0.7125   0.0304
  -1.750   0.3937   0.00949   0.00250  -0.1332   0.7007   0.0310
  -1.500   0.4218   0.00937   0.00233  -0.1331   0.6883   0.0315
  -1.250   0.4498   0.00928   0.00217  -0.1330   0.6743   0.0322
  -1.000   0.4775   0.00922   0.00204  -0.1328   0.6576   0.0328
  -0.750   0.5050   0.00919   0.00192  -0.1326   0.6373   0.0335
  -0.500   0.5322   0.00922   0.00183  -0.1323   0.6111   0.0341
  -0.250   0.5590   0.00929   0.00177  -0.1320   0.5856   0.0350
   0.000   0.5860   0.00935   0.00171  -0.1317   0.5672   0.0374
   0.250   0.6131   0.00942   0.00170  -0.1315   0.5518   0.0401
   0.750   0.6677   0.00920   0.00180  -0.1314   0.5252   0.2082
   1.000   0.6948   0.00929   0.00191  -0.1312   0.5156   0.2412
   1.250   0.7226   0.00933   0.00199  -0.1311   0.5100   0.2608
   1.500   0.7502   0.00940   0.00208  -0.1309   0.5041   0.2778
   1.750   0.7776   0.00947   0.00218  -0.1308   0.4970   0.2954
   2.000   0.8051   0.00953   0.00227  -0.1306   0.4889   0.3088
   2.250   0.8324   0.00961   0.00236  -0.1304   0.4822   0.3223
   2.500   0.8600   0.00963   0.00247  -0.1303   0.4741   0.3454
   2.750   0.8872   0.00966   0.00258  -0.1302   0.4648   0.3787
   3.000   0.9142   0.00965   0.00274  -0.1300   0.4520   0.4643
   3.250   0.9410   0.00965   0.00290  -0.1298   0.4369   0.5480
   3.500   0.9677   0.00962   0.00304  -0.1296   0.4231   0.6298
   4.000   1.0165   0.00932   0.00326  -0.1279   0.3883   1.0000
   4.250   1.0416   0.00966   0.00345  -0.1274   0.3565   1.0000
   4.500   1.0656   0.01012   0.00371  -0.1268   0.3190   1.0000
   4.750   1.0885   0.01072   0.00406  -0.1260   0.2745   1.0000
   5.000   1.1123   0.01122   0.00440  -0.1253   0.2430   1.0000
   5.250   1.1367   0.01164   0.00471  -0.1248   0.2214   1.0000
   5.500   1.1610   0.01205   0.00503  -0.1242   0.2003   1.0000
   5.750   1.1848   0.01251   0.00538  -0.1235   0.1759   1.0000
   6.000   1.2069   0.01315   0.00582  -0.1227   0.1395   1.0000
   6.250   1.2293   0.01374   0.00627  -0.1218   0.1158   1.0000
   6.500   1.2526   0.01420   0.00670  -0.1211   0.1029   1.0000
   6.750   1.2755   0.01469   0.00712  -0.1203   0.0900   1.0000
   7.000   1.2982   0.01517   0.00756  -0.1195   0.0771   1.0000
   7.250   1.3170   0.01605   0.00820  -0.1181   0.0439   1.0000
   7.500   1.3381   0.01666   0.00879  -0.1171   0.0367   1.0000
   7.750   1.3594   0.01721   0.00935  -0.1160   0.0328   1.0000
   8.000   1.3814   0.01767   0.00986  -0.1151   0.0310   1.0000
   8.250   1.4027   0.01817   0.01042  -0.1140   0.0293   1.0000
   8.500   1.4228   0.01876   0.01105  -0.1128   0.0273   1.0000
   8.750   1.4411   0.01948   0.01182  -0.1113   0.0252   1.0000
   9.000   1.4616   0.01996   0.01235  -0.1102   0.0242   1.0000
   9.250   1.4810   0.02050   0.01295  -0.1089   0.0228   1.0000
   9.500   1.4993   0.02109   0.01360  -0.1075   0.0212   1.0000
   9.750   1.5154   0.02181   0.01435  -0.1057   0.0197   1.0000
  10.000   1.5303   0.02247   0.01507  -0.1037   0.0186   1.0000
  10.250   1.5446   0.02312   0.01579  -0.1016   0.0176   1.0000
  10.500   1.5580   0.02384   0.01656  -0.0995   0.0165   1.0000
  10.750   1.5704   0.02464   0.01740  -0.0973   0.0155   1.0000
  11.000   1.5803   0.02562   0.01843  -0.0949   0.0146   1.0000
  11.250   1.5917   0.02652   0.01942  -0.0928   0.0139   1.0000
  11.500   1.6022   0.02751   0.02050  -0.0907   0.0132   1.0000
  11.750   1.6116   0.02861   0.02167  -0.0886   0.0125   1.0000
  12.000   1.6199   0.02985   0.02297  -0.0866   0.0120   1.0000
  12.250   1.6258   0.03132   0.02451  -0.0845   0.0114   1.0000
  12.500   1.6304   0.03298   0.02627  -0.0824   0.0110   1.0000
  12.750   1.6359   0.03462   0.02803  -0.0806   0.0107   1.0000
  13.000   1.6405   0.03643   0.02995  -0.0790   0.0104   1.0000
  13.250   1.6441   0.03842   0.03205  -0.0775   0.0100   1.0000
  13.500   1.6472   0.04055   0.03428  -0.0762   0.0097   1.0000
  13.750   1.6498   0.04282   0.03666  -0.0752   0.0094   1.0000
  14.000   1.6511   0.04534   0.03928  -0.0743   0.0091   1.0000
  14.250   1.6504   0.04814   0.04218  -0.0735   0.0088   1.0000
  14.500   1.6473   0.05136   0.04551  -0.0730   0.0086   1.0000
  14.750   1.6405   0.05512   0.04939  -0.0726   0.0084   1.0000
  15.000   1.6373   0.05857   0.05297  -0.0725   0.0082   1.0000
  15.250   1.6331   0.06228   0.05682  -0.0727   0.0081   1.0000
  15.500   1.6277   0.06631   0.06098  -0.0730   0.0079   1.0000
  15.750   1.6212   0.07060   0.06541  -0.0737   0.0078   1.0000
  16.000   1.6137   0.07515   0.07010  -0.0745   0.0077   1.0000
  16.250   1.6056   0.07988   0.07497  -0.0755   0.0076   1.0000
  16.500   1.5964   0.08484   0.08005  -0.0766   0.0075   1.0000
  16.750   1.5864   0.08997   0.08531  -0.0780   0.0074   1.0000
  17.000   1.5758   0.09531   0.09078  -0.0795   0.0073   1.0000
  17.250   1.5649   0.10082   0.09642  -0.0812   0.0072   1.0000
  17.500   1.5535   0.10649   0.10222  -0.0831   0.0071   1.0000
  17.750   1.5418   0.11231   0.10817  -0.0852   0.0070   1.0000
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