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DF102 (df102-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DF102 (df102-il)
Reynolds number: 50,000
Max Cl/Cd: 32.62 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-df102-il-50000-n5.txt
Download as CSV file: xf-df102-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4539   0.09961   0.09239  -0.0334   1.0000   0.0513
 -10.000  -0.4591   0.09447   0.08733  -0.0358   1.0000   0.0509
  -9.750  -0.4673   0.08881   0.08176  -0.0386   1.0000   0.0503
  -9.500  -0.4800   0.08218   0.07524  -0.0422   1.0000   0.0497
  -9.000  -0.5668   0.06335   0.05622  -0.0544   1.0000   0.0455
  -8.750  -0.5834   0.05937   0.05208  -0.0537   1.0000   0.0455
  -8.500  -0.5961   0.05563   0.04811  -0.0522   1.0000   0.0456
  -8.250  -0.6016   0.05223   0.04455  -0.0504   1.0000   0.0461
  -8.000  -0.6029   0.04915   0.04125  -0.0485   1.0000   0.0465
  -7.750  -0.6011   0.04629   0.03817  -0.0464   1.0000   0.0472
  -7.500  -0.5966   0.04364   0.03528  -0.0443   1.0000   0.0480
  -7.250  -0.5895   0.04139   0.03280  -0.0423   1.0000   0.0497
  -7.000  -0.5807   0.03922   0.03034  -0.0402   1.0000   0.0523
  -6.750  -0.5701   0.03695   0.02764  -0.0382   1.0000   0.0549
  -6.500  -0.5569   0.03478   0.02505  -0.0362   1.0000   0.0570
  -6.250  -0.5427   0.03301   0.02320  -0.0344   1.0000   0.0592
  -6.000  -0.5275   0.03157   0.02163  -0.0326   1.0000   0.0631
  -5.750  -0.5107   0.03017   0.01987  -0.0309   1.0000   0.0684
  -5.500  -0.4950   0.02884   0.01861  -0.0292   1.0000   0.0732
  -5.250  -0.4776   0.02763   0.01723  -0.0275   1.0000   0.0792
  -5.000  -0.4607   0.02654   0.01614  -0.0259   1.0000   0.0888
  -4.750  -0.4429   0.02549   0.01506  -0.0245   1.0000   0.1038
  -4.500  -0.4243   0.02446   0.01417  -0.0233   1.0000   0.1293
  -4.250  -0.4051   0.02371   0.01361  -0.0223   1.0000   0.1794
  -4.000  -0.3867   0.02339   0.01341  -0.0212   1.0000   0.2302
  -3.750  -0.3649   0.02328   0.01333  -0.0208   0.9979   0.2792
  -3.500  -0.3307   0.02318   0.01319  -0.0226   0.9899   0.3264
  -3.250  -0.2942   0.02299   0.01293  -0.0247   0.9826   0.3613
  -3.000  -0.2602   0.02272   0.01261  -0.0261   0.9744   0.3916
  -2.750  -0.2245   0.02247   0.01235  -0.0279   0.9670   0.4235
  -2.500  -0.1903   0.02221   0.01214  -0.0293   0.9587   0.4587
  -2.250  -0.1575   0.02195   0.01199  -0.0304   0.9505   0.5009
  -2.000  -0.1236   0.02168   0.01189  -0.0316   0.9426   0.5572
  -1.750  -0.0952   0.02136   0.01187  -0.0314   0.9336   0.6294
  -1.500  -0.0583   0.02106   0.01199  -0.0321   0.9271   0.7424
  -1.250   0.0170   0.02105   0.01211  -0.0400   0.9250   0.9212
  -1.000   0.0816   0.02117   0.01195  -0.0477   0.9193   1.0000
  -0.750   0.1218   0.02130   0.01184  -0.0505   0.9112   1.0000
  -0.500   0.1502   0.02145   0.01181  -0.0511   0.8994   1.0000
  -0.250   0.1810   0.02160   0.01180  -0.0520   0.8885   1.0000
   0.000   0.2196   0.02170   0.01176  -0.0542   0.8802   1.0000
   0.250   0.2469   0.02186   0.01182  -0.0543   0.8684   1.0000
   0.500   0.2738   0.02203   0.01189  -0.0542   0.8567   1.0000
   0.750   0.3037   0.02217   0.01195  -0.0546   0.8459   1.0000
   1.000   0.3387   0.02221   0.01195  -0.0557   0.8365   1.0000
   1.250   0.3658   0.02229   0.01198  -0.0553   0.8230   1.0000
   1.500   0.3979   0.02212   0.01177  -0.0553   0.8076   1.0000
   1.750   0.4270   0.02185   0.01145  -0.0544   0.7879   1.0000
   2.000   0.4555   0.02152   0.01108  -0.0533   0.7667   1.0000
   2.250   0.4857   0.02119   0.01071  -0.0525   0.7476   1.0000
   2.500   0.5101   0.02113   0.01063  -0.0511   0.7286   1.0000
   2.750   0.5344   0.02107   0.01058  -0.0497   0.7087   1.0000
   3.000   0.5609   0.02095   0.01043  -0.0485   0.6886   1.0000
   3.250   0.5839   0.02096   0.01042  -0.0469   0.6653   1.0000
   3.500   0.6088   0.02090   0.01034  -0.0454   0.6408   1.0000
   3.750   0.6317   0.02094   0.01033  -0.0438   0.6129   1.0000
   4.000   0.6534   0.02103   0.01036  -0.0419   0.5807   1.0000
   4.250   0.6738   0.02120   0.01047  -0.0400   0.5436   1.0000
   4.500   0.6936   0.02144   0.01058  -0.0379   0.5011   1.0000
   4.750   0.7121   0.02183   0.01074  -0.0358   0.4525   1.0000
   5.000   0.7294   0.02240   0.01101  -0.0337   0.4047   1.0000
   5.250   0.7461   0.02314   0.01148  -0.0317   0.3639   1.0000
   5.500   0.7631   0.02397   0.01205  -0.0300   0.3323   1.0000
   5.750   0.7813   0.02482   0.01272  -0.0285   0.3085   1.0000
   6.000   0.8004   0.02568   0.01345  -0.0272   0.2894   1.0000
   6.250   0.8205   0.02656   0.01425  -0.0262   0.2736   1.0000
   6.500   0.8421   0.02744   0.01509  -0.0253   0.2601   1.0000
   6.750   0.8651   0.02833   0.01597  -0.0246   0.2485   1.0000
   7.000   0.8884   0.02925   0.01685  -0.0240   0.2380   1.0000
   7.250   0.9116   0.03018   0.01783  -0.0234   0.2280   1.0000
   7.500   0.9358   0.03117   0.01892  -0.0230   0.2196   1.0000
   7.750   0.9609   0.03219   0.01997  -0.0226   0.2126   1.0000
   8.000   0.9843   0.03330   0.02123  -0.0221   0.2054   1.0000
   8.250   1.0072   0.03438   0.02241  -0.0216   0.1987   1.0000
   8.500   1.0292   0.03559   0.02376  -0.0209   0.1924   1.0000
   8.750   1.0506   0.03688   0.02525  -0.0203   0.1869   1.0000
   9.000   1.0748   0.03817   0.02660  -0.0200   0.1826   1.0000
   9.250   1.0934   0.03973   0.02844  -0.0190   0.1781   1.0000
   9.500   1.1098   0.04128   0.03029  -0.0179   0.1731   1.0000
   9.750   1.1301   0.04260   0.03169  -0.0172   0.1687   1.0000
  10.000   1.1456   0.04435   0.03368  -0.0160   0.1649   1.0000
  10.250   1.1552   0.04648   0.03621  -0.0144   0.1615   1.0000
  10.500   1.1659   0.04853   0.03855  -0.0129   0.1582   1.0000
  10.750   1.1809   0.05024   0.04042  -0.0118   0.1548   1.0000
  11.000   1.1929   0.05219   0.04256  -0.0106   0.1516   1.0000
  11.250   1.1833   0.05507   0.04589  -0.0077   0.1487   1.0000
  11.500   1.1748   0.05789   0.04903  -0.0051   0.1461   1.0000
  11.750   1.1656   0.06069   0.05207  -0.0025   0.1440   1.0000
  12.000   1.1566   0.06362   0.05519  -0.0005   0.1421   1.0000
  12.250   1.1611   0.06588   0.05757   0.0007   0.1398   1.0000
  12.500   1.1496   0.06927   0.06111   0.0019   0.1380   1.0000
  12.750   1.1052   0.07560   0.06767   0.0021   0.1377   1.0000
  13.000   1.0453   0.08538   0.07758  -0.0014   0.1378   1.0000
  13.250   0.9460   0.10582   0.09794  -0.0138   0.1379   1.0000
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