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GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 484 AIRFOIL (goe484-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.74 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe484-il-1000000.txt
Download as CSV file: xf-goe484-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 484 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3874   0.12953   0.12777  -0.0280   1.0000   0.0135
 -11.250  -0.3870   0.12648   0.12473  -0.0286   1.0000   0.0135
 -11.000  -0.3861   0.12348   0.12174  -0.0288   1.0000   0.0135
 -10.750  -0.3830   0.12016   0.11844  -0.0278   1.0000   0.0138
 -10.500  -0.3807   0.11780   0.11609  -0.0273   1.0000   0.0139
 -10.250  -0.3779   0.11584   0.11414  -0.0267   1.0000   0.0140
 -10.000  -0.3760   0.11392   0.11224  -0.0259   1.0000   0.0143
  -9.750  -0.3695   0.11105   0.10937  -0.0271   0.9997   0.0145
  -9.500  -0.3547   0.10766   0.10598  -0.0305   0.9988   0.0152
  -9.250  -0.3399   0.10373   0.10204  -0.0344   0.9975   0.0165
  -9.000  -0.3276   0.09863   0.09695  -0.0418   0.9956   0.0169
  -8.750  -0.3129   0.09416   0.09246  -0.0470   0.9943   0.0170
  -8.500  -0.3005   0.09007   0.08837  -0.0509   0.9915   0.0170
  -8.250  -0.2900   0.08523   0.08353  -0.0540   0.9891   0.0173
  -8.000  -0.2713   0.08266   0.08096  -0.0564   0.9874   0.0176
  -7.750  -0.2521   0.07968   0.07797  -0.0603   0.9855   0.0178
  -7.500  -0.2309   0.07659   0.07488  -0.0650   0.9839   0.0184
  -7.250  -0.2155   0.07339   0.07168  -0.0686   0.9783   0.0191
  -7.000  -0.1810   0.06696   0.06522  -0.0828   0.9743   0.0211
  -6.750  -0.1496   0.06175   0.05998  -0.0922   0.9725   0.0212
  -6.500  -0.1136   0.05583   0.05400  -0.1030   0.9711   0.0212
  -6.250  -0.0957   0.05053   0.04868  -0.1088   0.9644   0.0219
  -6.000  -0.0670   0.04823   0.04634  -0.1128   0.9612   0.0223
  -5.750  -0.0336   0.04530   0.04337  -0.1186   0.9584   0.0231
  -5.500  -0.0052   0.04168   0.03968  -0.1238   0.9509   0.0242
  -5.250   0.0400   0.03500   0.03277  -0.1336   0.9446   0.0264
  -5.000   0.0646   0.02283   0.01998  -0.1417   0.9331   0.0274
  -4.750   0.0918   0.02178   0.01887  -0.1426   0.9282   0.0278
  -4.500   0.1159   0.02065   0.01765  -0.1428   0.9209   0.0284
  -4.250   0.1429   0.01910   0.01593  -0.1435   0.9150   0.0294
  -4.000   0.1684   0.01731   0.01392  -0.1437   0.9078   0.0310
  -3.750   0.1975   0.01747   0.01390  -0.1434   0.9020   0.0331
  -3.500   0.2242   0.01645   0.01264  -0.1434   0.8960   0.0332
  -3.250   0.2474   0.01256   0.00831  -0.1439   0.8894   0.0351
  -3.000   0.2743   0.01192   0.00762  -0.1439   0.8843   0.0362
  -2.750   0.3007   0.01135   0.00698  -0.1437   0.8784   0.0376
  -2.500   0.3284   0.00967   0.00491  -0.1430   0.8729   0.0313
  -2.250   0.3554   0.00901   0.00414  -0.1428   0.8676   0.0310
  -2.000   0.3823   0.00853   0.00357  -0.1424   0.8615   0.0310
  -1.500   0.4362   0.00776   0.00269  -0.1418   0.8498   0.0308
  -1.250   0.4632   0.00748   0.00237  -0.1415   0.8437   0.0309
  -1.000   0.4902   0.00726   0.00213  -0.1412   0.8379   0.0314
  -0.750   0.5169   0.00704   0.00188  -0.1408   0.8308   0.0315
  -0.500   0.5437   0.00686   0.00167  -0.1404   0.8227   0.0318
  -0.250   0.5701   0.00674   0.00150  -0.1399   0.8126   0.0324
   0.000   0.5965   0.00664   0.00138  -0.1395   0.8014   0.0330
   0.250   0.6220   0.00657   0.00124  -0.1388   0.7837   0.0336
   0.500   0.6471   0.00651   0.00109  -0.1380   0.7611   0.0348
   0.750   0.6717   0.00653   0.00101  -0.1371   0.7326   0.0362
   1.000   0.6940   0.00669   0.00098  -0.1357   0.6838   0.0378
   1.250   0.7165   0.00691   0.00101  -0.1345   0.6442   0.0407
   1.500   0.7396   0.00700   0.00111  -0.1335   0.6114   0.1060
   1.750   0.7639   0.00706   0.00125  -0.1327   0.5888   0.1726
   2.000   0.7879   0.00690   0.00141  -0.1321   0.5661   0.3614
   2.250   0.8101   0.00662   0.00163  -0.1312   0.5420   0.6290
   2.500   0.8396   0.00614   0.00179  -0.1316   0.5138   1.0000
   2.750   0.8623   0.00649   0.00192  -0.1305   0.4670   1.0000
   3.000   0.8755   0.00766   0.00234  -0.1278   0.3099   1.0000
   3.250   0.8842   0.00942   0.00308  -0.1246   0.0986   1.0000
   3.500   0.9055   0.01003   0.00346  -0.1233   0.0491   1.0000
   3.750   0.9302   0.01029   0.00370  -0.1226   0.0449   1.0000
   4.000   0.9543   0.01061   0.00399  -0.1218   0.0406   1.0000
   4.250   0.9784   0.01092   0.00432  -0.1210   0.0387   1.0000
   4.500   1.0031   0.01116   0.00457  -0.1204   0.0379   1.0000
   4.750   1.0274   0.01142   0.00484  -0.1196   0.0366   1.0000
   5.000   1.0515   0.01171   0.00513  -0.1189   0.0351   1.0000
   5.250   1.0751   0.01203   0.00545  -0.1181   0.0338   1.0000
   5.500   1.0979   0.01243   0.00586  -0.1171   0.0323   1.0000
   5.750   1.1165   0.01321   0.00672  -0.1153   0.0303   1.0000
   6.000   1.1401   0.01348   0.00700  -0.1145   0.0298   1.0000
   6.250   1.1635   0.01377   0.00731  -0.1137   0.0291   1.0000
   6.500   1.1866   0.01408   0.00764  -0.1128   0.0280   1.0000
   6.750   1.2094   0.01439   0.00795  -0.1119   0.0268   1.0000
   7.000   1.2317   0.01474   0.00830  -0.1109   0.0258   1.0000
   7.250   1.2523   0.01522   0.00878  -0.1097   0.0247   1.0000
   7.500   1.2662   0.01630   0.00994  -0.1072   0.0232   1.0000
   7.750   1.2901   0.01644   0.01011  -0.1065   0.0226   1.0000
   8.000   1.3126   0.01670   0.01038  -0.1056   0.0217   1.0000
   8.250   1.3341   0.01702   0.01073  -0.1045   0.0208   1.0000
   8.500   1.3556   0.01732   0.01103  -0.1035   0.0199   1.0000
   8.750   1.3753   0.01775   0.01145  -0.1022   0.0190   1.0000
   9.000   1.3859   0.01883   0.01261  -0.0992   0.0179   1.0000
   9.250   1.4058   0.01908   0.01290  -0.0979   0.0175   1.0000
   9.500   1.4250   0.01936   0.01321  -0.0964   0.0167   1.0000
   9.750   1.4430   0.01972   0.01360  -0.0948   0.0160   1.0000
  10.000   1.4607   0.02009   0.01400  -0.0931   0.0154   1.0000
  10.250   1.4770   0.02056   0.01447  -0.0913   0.0147   1.0000
  10.500   1.4820   0.02193   0.01593  -0.0877   0.0139   1.0000
  10.750   1.4979   0.02246   0.01653  -0.0859   0.0136   1.0000
  11.000   1.5118   0.02315   0.01729  -0.0839   0.0133   1.0000
  11.250   1.5267   0.02376   0.01797  -0.0821   0.0127   1.0000
  11.500   1.5411   0.02438   0.01864  -0.0803   0.0123   1.0000
  11.750   1.5546   0.02508   0.01939  -0.0784   0.0119   1.0000
  12.000   1.5679   0.02579   0.02013  -0.0766   0.0114   1.0000
  12.250   1.5759   0.02698   0.02138  -0.0741   0.0110   1.0000
  12.500   1.5758   0.02901   0.02357  -0.0709   0.0105   1.0000
  12.750   1.5854   0.03014   0.02480  -0.0689   0.0104   1.0000
  13.000   1.5948   0.03131   0.02607  -0.0670   0.0102   1.0000
  13.250   1.6030   0.03262   0.02749  -0.0651   0.0099   1.0000
  13.500   1.6096   0.03410   0.02908  -0.0632   0.0097   1.0000
  13.750   1.6158   0.03565   0.03073  -0.0614   0.0095   1.0000
  14.000   1.6220   0.03721   0.03239  -0.0597   0.0092   1.0000
  14.250   1.6271   0.03891   0.03419  -0.0582   0.0090   1.0000
  14.500   1.6317   0.04071   0.03608  -0.0567   0.0088   1.0000
  14.750   1.6334   0.04289   0.03837  -0.0553   0.0087   1.0000
  15.000   1.6351   0.04511   0.04068  -0.0541   0.0085   1.0000
  15.250   1.6327   0.04792   0.04361  -0.0530   0.0084   1.0000
  15.500   1.6247   0.05156   0.04740  -0.0521   0.0082   1.0000
  15.750   1.6116   0.05609   0.05212  -0.0516   0.0080   1.0000
  16.000   1.5928   0.06177   0.05804  -0.0518   0.0079   1.0000
  16.250   1.5780   0.06720   0.06367  -0.0526   0.0078   1.0000
  16.500   1.5739   0.07126   0.06787  -0.0535   0.0078   1.0000
  16.750   1.5641   0.07642   0.07319  -0.0550   0.0077   1.0000
  17.000   1.5535   0.08194   0.07886  -0.0569   0.0077   1.0000
  17.250   1.5404   0.08814   0.08523  -0.0594   0.0076   1.0000
  17.500   1.5225   0.09557   0.09284  -0.0628   0.0076   1.0000
  17.750   1.5047   0.10337   0.10080  -0.0668   0.0076   1.0000
  18.000   1.4817   0.11273   0.11034  -0.0720   0.0076   1.0000
  18.250   1.4555   0.12348   0.12129  -0.0785   0.0076   1.0000
  18.500   1.4184   0.13768   0.13571  -0.0875   0.0077   1.0000
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