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GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 572 AIRFOIL (goe572-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103.81 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe572-il-1000000.txt
Download as CSV file: xf-goe572-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 572 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2484   0.02720   0.02320  -0.1525   0.5937   0.0155
 -11.000  -0.2674   0.02477   0.02047  -0.1464   0.5865   0.0157
 -10.750  -0.2621   0.02372   0.01925  -0.1431   0.5793   0.0160
 -10.500  -0.2625   0.02230   0.01759  -0.1389   0.5722   0.0162
 -10.250  -0.2545   0.02137   0.01648  -0.1357   0.5652   0.0164
 -10.000  -0.2500   0.02015   0.01503  -0.1319   0.5589   0.0167
  -9.750  -0.2424   0.01922   0.01394  -0.1285   0.5524   0.0171
  -9.500  -0.2249   0.01885   0.01352  -0.1265   0.5471   0.0174
  -9.250  -0.2055   0.01870   0.01333  -0.1249   0.5408   0.0177
  -9.000  -0.1819   0.01890   0.01352  -0.1239   0.5352   0.0181
  -8.750  -0.1670   0.01823   0.01273  -0.1214   0.5302   0.0185
  -8.500  -0.1510   0.01769   0.01205  -0.1192   0.5249   0.0189
  -8.250  -0.1337   0.01732   0.01155  -0.1171   0.5196   0.0194
  -8.000  -0.1137   0.01699   0.01111  -0.1154   0.5157   0.0198
  -7.750  -0.0990   0.01621   0.01017  -0.1129   0.5114   0.0203
  -7.500  -0.0791   0.01609   0.01002  -0.1113   0.5059   0.0209
  -7.250  -0.0588   0.01590   0.00980  -0.1097   0.5019   0.0214
  -7.000  -0.0371   0.01575   0.00961  -0.1084   0.4981   0.0219
  -6.750  -0.0160   0.01559   0.00938  -0.1069   0.4939   0.0226
  -6.500   0.0029   0.01524   0.00891  -0.1050   0.4891   0.0231
  -6.250   0.0238   0.01503   0.00859  -0.1034   0.4855   0.0237
  -6.000   0.0428   0.01442   0.00787  -0.1016   0.4817   0.0243
  -5.750   0.0629   0.01406   0.00749  -0.1000   0.4779   0.0250
  -5.500   0.0842   0.01404   0.00743  -0.0985   0.4737   0.0257
  -5.250   0.1055   0.01397   0.00731  -0.0971   0.4697   0.0264
  -5.000   0.1274   0.01369   0.00699  -0.0958   0.4664   0.0271
  -4.750   0.1490   0.01349   0.00671  -0.0943   0.4624   0.0278
  -4.500   0.1699   0.01339   0.00653  -0.0927   0.4584   0.0283
  -4.250   0.1872   0.01286   0.00591  -0.0905   0.4543   0.0293
  -4.000   0.2079   0.01261   0.00567  -0.0890   0.4516   0.0301
  -3.750   0.2288   0.01252   0.00557  -0.0874   0.4479   0.0309
  -3.500   0.2485   0.01236   0.00535  -0.0856   0.4438   0.0318
  -3.250   0.2676   0.01225   0.00518  -0.0837   0.4397   0.0325
  -3.000   0.2891   0.01213   0.00503  -0.0823   0.4367   0.0333
  -2.750   0.3099   0.01190   0.00476  -0.0807   0.4330   0.0341
  -2.500   0.3286   0.01160   0.00442  -0.0788   0.4292   0.0350
  -2.250   0.3482   0.01151   0.00430  -0.0770   0.4252   0.0361
  -2.000   0.3687   0.01142   0.00418  -0.0754   0.4215   0.0369
  -1.750   0.3903   0.01131   0.00406  -0.0741   0.4182   0.0379
  -1.500   0.4113   0.01127   0.00399  -0.0726   0.4147   0.0390
  -1.250   0.4315   0.01126   0.00394  -0.0710   0.4109   0.0397
  -1.000   0.4495   0.01114   0.00377  -0.0689   0.4068   0.0412
  -0.750   0.4717   0.01106   0.00369  -0.0677   0.4037   0.0430
  -0.500   0.4933   0.01104   0.00366  -0.0664   0.4000   0.0443
  -0.250   0.5138   0.01107   0.00365  -0.0649   0.3957   0.0461
   0.000   0.5334   0.01110   0.00363  -0.0633   0.3912   0.0486
   0.250   0.5558   0.01105   0.00361  -0.0621   0.3886   0.0528
   0.500   0.5774   0.01108   0.00361  -0.0609   0.3851   0.0553
   0.750   0.5978   0.01108   0.00362  -0.0595   0.3814   0.0653
   1.000   0.6171   0.01112   0.00369  -0.0579   0.3773   0.0841
   1.250   0.6393   0.01105   0.00375  -0.0569   0.3742   0.1270
   1.500   0.6622   0.01086   0.00385  -0.0562   0.3710   0.2382
   1.750   0.6894   0.01044   0.00403  -0.0567   0.3675   0.4735
   2.000   1.0875   0.01066   0.00515  -0.1383   0.3521   1.0000
   2.250   1.1035   0.01079   0.00524  -0.1361   0.3489   1.0000
   2.500   1.1172   0.01094   0.00535  -0.1335   0.3455   1.0000
   2.750   1.1333   0.01101   0.00542  -0.1312   0.3434   1.0000
   3.000   1.1488   0.01111   0.00550  -0.1289   0.3410   1.0000
   3.250   1.1640   0.01123   0.00560  -0.1266   0.3380   1.0000
   3.500   1.1789   0.01139   0.00573  -0.1242   0.3348   1.0000
   3.750   1.1932   0.01159   0.00589  -0.1217   0.3315   1.0000
   4.000   1.2107   0.01171   0.00601  -0.1199   0.3294   1.0000
   4.250   1.2285   0.01184   0.00614  -0.1181   0.3268   1.0000
   4.500   1.2457   0.01200   0.00629  -0.1163   0.3246   1.0000
   4.750   1.2620   0.01220   0.00647  -0.1144   0.3215   1.0000
   5.000   1.2772   0.01244   0.00668  -0.1122   0.3187   1.0000
   5.250   1.2915   0.01270   0.00693  -0.1099   0.3156   1.0000
   5.500   1.3104   0.01285   0.00709  -0.1086   0.3138   1.0000
   5.750   1.3283   0.01304   0.00729  -0.1070   0.3119   1.0000
   6.000   1.3450   0.01327   0.00752  -0.1053   0.3095   1.0000
   6.250   1.3609   0.01354   0.00778  -0.1035   0.3070   1.0000
   6.500   1.3739   0.01391   0.00812  -0.1012   0.3028   1.0000
   6.750   1.3883   0.01425   0.00847  -0.0992   0.3010   1.0000
   7.000   1.4076   0.01445   0.00869  -0.0981   0.2986   1.0000
   7.250   1.4242   0.01475   0.00901  -0.0966   0.2969   1.0000
   7.500   1.4399   0.01509   0.00936  -0.0950   0.2940   1.0000
   7.750   1.4534   0.01553   0.00979  -0.0931   0.2909   1.0000
   8.000   1.4643   0.01609   0.01034  -0.0908   0.2863   1.0000
   8.250   1.4815   0.01643   0.01071  -0.0897   0.2845   1.0000
   8.500   1.4971   0.01685   0.01115  -0.0883   0.2823   1.0000
   8.750   1.5100   0.01741   0.01171  -0.0866   0.2783   1.0000
   9.000   1.5183   0.01821   0.01249  -0.0844   0.2733   1.0000
   9.250   1.5332   0.01874   0.01304  -0.0832   0.2704   1.0000
   9.500   1.5466   0.01936   0.01369  -0.0818   0.2670   1.0000
   9.750   1.5564   0.02020   0.01452  -0.0801   0.2631   1.0000
  10.000   1.5627   0.02128   0.01560  -0.0780   0.2579   1.0000
  10.250   1.5752   0.02205   0.01640  -0.0768   0.2541   1.0000
  10.500   1.5786   0.02342   0.01775  -0.0748   0.2472   1.0000
  10.750   1.5840   0.02473   0.01907  -0.0731   0.2406   1.0000
  11.000   1.5840   0.02650   0.02082  -0.0711   0.2336   1.0000
  11.250   1.5839   0.02837   0.02268  -0.0694   0.2254   1.0000
  11.500   1.5780   0.03078   0.02509  -0.0674   0.2182   1.0000
  11.750   1.5689   0.03359   0.02788  -0.0654   0.2080   1.0000
  12.000   1.5474   0.03760   0.03186  -0.0630   0.1947   1.0000
  12.250   1.5314   0.04133   0.03559  -0.0612   0.1841   1.0000
  12.500   1.4819   0.04845   0.04265  -0.0584   0.1600   1.0000
  12.750   1.4671   0.05244   0.04668  -0.0573   0.1520   1.0000
  13.000   1.4336   0.05848   0.05272  -0.0557   0.1351   1.0000
  13.250   1.3962   0.06521   0.05949  -0.0544   0.1178   1.0000
  13.500   1.3786   0.06990   0.06424  -0.0538   0.1102   1.0000
  13.750   1.3532   0.07562   0.07001  -0.0531   0.0991   1.0000
  14.000   1.3223   0.08221   0.07664  -0.0527   0.0839   1.0000
  14.250   1.3012   0.08772   0.08217  -0.0524   0.0724   1.0000
  14.500   1.2771   0.09379   0.08825  -0.0524   0.0593   1.0000
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