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DF102 (df102-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DF102 (df102-il)
Reynolds number: 100,000
Max Cl/Cd: 45.49 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-df102-il-100000-n5.txt
Download as CSV file: xf-df102-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DF102                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4872   0.08854   0.08342  -0.0372   1.0000   0.0267
 -10.250  -0.5006   0.08125   0.07619  -0.0408   1.0000   0.0262
  -9.750  -0.6200   0.05395   0.04848  -0.0605   1.0000   0.0224
  -9.500  -0.6414   0.05034   0.04465  -0.0587   1.0000   0.0223
  -9.250  -0.6455   0.04820   0.04245  -0.0568   1.0000   0.0229
  -9.000  -0.6490   0.04604   0.04017  -0.0546   1.0000   0.0233
  -8.750  -0.6512   0.04384   0.03781  -0.0522   1.0000   0.0238
  -8.500  -0.6518   0.04177   0.03555  -0.0496   1.0000   0.0247
  -8.250  -0.6521   0.03942   0.03290  -0.0468   1.0000   0.0254
  -8.000  -0.6499   0.03703   0.03017  -0.0440   1.0000   0.0259
  -7.750  -0.6446   0.03470   0.02746  -0.0414   1.0000   0.0265
  -7.500  -0.6361   0.03262   0.02502  -0.0389   1.0000   0.0270
  -7.250  -0.6249   0.03075   0.02278  -0.0365   1.0000   0.0278
  -7.000  -0.6123   0.02897   0.02081  -0.0345   1.0000   0.0287
  -6.750  -0.5952   0.02772   0.01953  -0.0334   0.9991   0.0304
  -6.500  -0.5634   0.02638   0.01799  -0.0349   0.9943   0.0333
  -6.250  -0.5325   0.02498   0.01634  -0.0358   0.9891   0.0354
  -6.000  -0.5016   0.02356   0.01484  -0.0370   0.9842   0.0381
  -5.750  -0.4709   0.02262   0.01381  -0.0381   0.9786   0.0426
  -5.500  -0.4393   0.02162   0.01265  -0.0391   0.9730   0.0462
  -5.250  -0.4070   0.02067   0.01165  -0.0404   0.9680   0.0524
  -5.000  -0.3776   0.01980   0.01072  -0.0411   0.9613   0.0611
  -4.750  -0.3435   0.01886   0.00981  -0.0426   0.9566   0.0795
  -4.500  -0.3156   0.01796   0.00923  -0.0431   0.9496   0.1316
  -4.250  -0.2817   0.01750   0.00890  -0.0445   0.9441   0.1865
  -4.000  -0.2473   0.01722   0.00870  -0.0460   0.9388   0.2308
  -3.750  -0.2171   0.01702   0.00859  -0.0466   0.9314   0.2741
  -3.500  -0.1807   0.01677   0.00834  -0.0484   0.9268   0.3052
  -3.250  -0.1528   0.01654   0.00808  -0.0483   0.9185   0.3264
  -3.000  -0.1183   0.01624   0.00779  -0.0495   0.9129   0.3487
  -2.750  -0.0897   0.01600   0.00757  -0.0496   0.9049   0.3718
  -2.500  -0.0572   0.01570   0.00732  -0.0503   0.8985   0.3991
  -2.250  -0.0287   0.01544   0.00715  -0.0503   0.8905   0.4299
  -2.000   0.0023   0.01514   0.00696  -0.0507   0.8835   0.4700
  -1.750   0.0296   0.01485   0.00684  -0.0503   0.8749   0.5190
  -1.500   0.0602   0.01451   0.00671  -0.0504   0.8679   0.5842
  -1.250   0.0858   0.01422   0.00667  -0.0495   0.8587   0.6573
  -1.000   0.1180   0.01388   0.00662  -0.0494   0.8522   0.7470
  -0.750   0.1610   0.01375   0.00670  -0.0513   0.8447   0.8454
  -0.500   0.2121   0.01368   0.00662  -0.0552   0.8385   0.9130
  -0.250   0.2574   0.01366   0.00654  -0.0584   0.8300   0.9523
   0.000   0.3081   0.01351   0.00628  -0.0625   0.8210   0.9770
   0.250   0.3562   0.01331   0.00599  -0.0662   0.8050   0.9976
   0.500   0.3812   0.01323   0.00580  -0.0653   0.7858   1.0000
   0.750   0.4036   0.01316   0.00562  -0.0638   0.7666   1.0000
   1.000   0.4269   0.01310   0.00543  -0.0625   0.7473   1.0000
   1.250   0.4488   0.01311   0.00534  -0.0610   0.7265   1.0000
   1.500   0.4716   0.01314   0.00528  -0.0596   0.7071   1.0000
   1.750   0.4947   0.01320   0.00524  -0.0584   0.6889   1.0000
   2.000   0.5175   0.01329   0.00523  -0.0571   0.6694   1.0000
   2.250   0.5400   0.01339   0.00527  -0.0558   0.6488   1.0000
   2.500   0.5626   0.01352   0.00528  -0.0545   0.6269   1.0000
   2.750   0.5845   0.01367   0.00536  -0.0531   0.6025   1.0000
   3.000   0.6062   0.01385   0.00543  -0.0516   0.5755   1.0000
   3.250   0.6273   0.01407   0.00554  -0.0501   0.5443   1.0000
   3.500   0.6479   0.01433   0.00564  -0.0484   0.5085   1.0000
   3.750   0.6674   0.01467   0.00579  -0.0467   0.4644   1.0000
   4.000   0.6857   0.01512   0.00599  -0.0448   0.4118   1.0000
   4.250   0.7027   0.01571   0.00625  -0.0428   0.3580   1.0000
   4.500   0.7199   0.01635   0.00661  -0.0410   0.3139   1.0000
   4.750   0.7380   0.01698   0.00702  -0.0394   0.2830   1.0000
   5.000   0.7571   0.01757   0.00748  -0.0380   0.2616   1.0000
   5.250   0.7766   0.01814   0.00795  -0.0366   0.2455   1.0000
   5.500   0.7965   0.01869   0.00843  -0.0353   0.2323   1.0000
   5.750   0.8166   0.01925   0.00893  -0.0341   0.2211   1.0000
   6.000   0.8365   0.01983   0.00947  -0.0328   0.2117   1.0000
   6.250   0.8577   0.02035   0.01002  -0.0317   0.2032   1.0000
   6.750   0.8992   0.02151   0.01117  -0.0296   0.1885   1.0000
   7.000   0.9194   0.02215   0.01178  -0.0284   0.1821   1.0000
   7.250   0.9409   0.02273   0.01243  -0.0275   0.1754   1.0000
   7.500   0.9617   0.02335   0.01308  -0.0265   0.1699   1.0000
   7.750   0.9829   0.02407   0.01378  -0.0256   0.1654   1.0000
   8.000   1.0046   0.02473   0.01457  -0.0247   0.1605   1.0000
   8.250   1.0257   0.02542   0.01532  -0.0238   0.1560   1.0000
   8.500   1.0466   0.02621   0.01609  -0.0229   0.1520   1.0000
   8.750   1.0675   0.02693   0.01699  -0.0220   0.1473   1.0000
   9.000   1.0881   0.02769   0.01785  -0.0211   0.1433   1.0000
   9.250   1.1090   0.02852   0.01872  -0.0202   0.1402   1.0000
   9.500   1.1305   0.02947   0.01975  -0.0195   0.1373   1.0000
   9.750   1.1502   0.03040   0.02091  -0.0185   0.1339   1.0000
  10.000   1.1691   0.03130   0.02196  -0.0175   0.1304   1.0000
  10.250   1.1878   0.03217   0.02290  -0.0165   0.1273   1.0000
  10.500   1.2085   0.03320   0.02396  -0.0158   0.1247   1.0000
  10.750   1.2246   0.03439   0.02547  -0.0145   0.1221   1.0000
  11.000   1.2395   0.03556   0.02690  -0.0130   0.1191   1.0000
  11.250   1.2538   0.03663   0.02814  -0.0115   0.1162   1.0000
  11.500   1.2688   0.03759   0.02920  -0.0102   0.1136   1.0000
  11.750   1.2863   0.03873   0.03034  -0.0093   0.1112   1.0000
  12.000   1.2890   0.04017   0.03220  -0.0065   0.1086   1.0000
  12.250   1.2903   0.04137   0.03367  -0.0036   0.1052   1.0000
  12.500   1.2939   0.04199   0.03436  -0.0012   0.1013   1.0000
  12.750   1.2972   0.04271   0.03508   0.0008   0.0975   1.0000
  13.000   1.2914   0.04443   0.03715   0.0032   0.0936   1.0000
  13.250   1.2899   0.04567   0.03854   0.0050   0.0895   1.0000
  13.500   1.2913   0.04681   0.03965   0.0062   0.0861   1.0000
  13.750   1.2859   0.04931   0.04249   0.0073   0.0828   1.0000
  14.000   1.2810   0.05184   0.04528   0.0079   0.0794   1.0000
  14.250   1.2775   0.05420   0.04777   0.0082   0.0762   1.0000
  14.500   1.2729   0.05685   0.05049   0.0080   0.0733   1.0000
  14.750   1.2602   0.06113   0.05513   0.0072   0.0700   1.0000
  15.000   1.2475   0.06559   0.05981   0.0058   0.0670   1.0000
  15.250   1.2347   0.07027   0.06464   0.0039   0.0644   1.0000
  15.500   1.2205   0.07551   0.06996   0.0014   0.0625   1.0000
  15.750   1.1944   0.08339   0.07811  -0.0025   0.0616   1.0000
  16.000   1.1635   0.09278   0.08769  -0.0077   0.0617   1.0000
  16.250   1.1267   0.10404   0.09910  -0.0141   0.0623   1.0000
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