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SG6043 (sg6043-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 100,000
Max Cl/Cd: 66.47 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6043-il-100000.txt
Download as CSV file: xf-sg6043-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6043                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3860   0.11161   0.10743  -0.0154   1.0000   0.0725
  -6.500  -0.4026   0.11086   0.10675  -0.0137   1.0000   0.0735
  -6.250  -0.4194   0.11012   0.10609  -0.0134   1.0000   0.0743
  -6.000  -0.4301   0.10894   0.10496  -0.0205   1.0000   0.0751
  -5.750  -0.4149   0.10346   0.09950  -0.0238   0.9961   0.0762
  -5.500  -0.3961   0.09947   0.09550  -0.0201   0.9919   0.0783
  -5.250  -0.3750   0.09595   0.09196  -0.0236   0.9865   0.0815
  -5.000  -0.3551   0.09215   0.08815  -0.0305   0.9796   0.0859
  -4.750  -0.3162   0.08561   0.08149  -0.0501   0.9721   0.0905
  -4.500  -0.3071   0.08285   0.07878  -0.0462   0.9669   0.0925
  -4.250  -0.2814   0.07954   0.07544  -0.0495   0.9621   0.0973
  -4.000  -0.2364   0.07318   0.06884  -0.0665   0.9546   0.1061
  -3.750  -0.1823   0.07002   0.06527  -0.0792   0.9490   0.1205
  -3.500  -0.1776   0.06581   0.06130  -0.0757   0.9435   0.1228
  -3.250  -0.1481   0.06326   0.05874  -0.0780   0.9387   0.1334
  -3.000  -0.1173   0.05960   0.05498  -0.0827   0.9328   0.1428
  -2.750  -0.0771   0.05616   0.05138  -0.0890   0.9274   0.1588
  -2.500  -0.0318   0.05313   0.04821  -0.0950   0.9238   0.1781
  -2.250   0.0857   0.04268   0.03568  -0.1152   0.9234   0.0896
  -2.000   0.1136   0.03964   0.03253  -0.1167   0.9169   0.0866
  -1.750   0.1613   0.03669   0.02896  -0.1207   0.9131   0.0797
  -1.500   0.2114   0.03470   0.02630  -0.1243   0.9100   0.0779
  -1.250   0.2401   0.03380   0.02523  -0.1248   0.9031   0.0802
  -1.000   0.2774   0.03316   0.02435  -0.1264   0.8977   0.0881
  -0.750   0.3232   0.03204   0.02321  -0.1294   0.8944   0.1015
  -0.500   0.3460   0.03150   0.02279  -0.1289   0.8860   0.1255
  -0.250   0.3864   0.03077   0.02236  -0.1313   0.8812   0.1950
   0.000   0.4236   0.02853   0.02233  -0.1321   0.8789   0.7828
   0.250   0.4364   0.02854   0.02228  -0.1292   0.8679   1.0000
   0.500   0.4814   0.02871   0.02210  -0.1321   0.8636   1.0000
   0.750   0.5013   0.02920   0.02242  -0.1312   0.8530   1.0000
   1.000   0.5456   0.02927   0.02226  -0.1339   0.8484   1.0000
   1.250   0.5659   0.02978   0.02265  -0.1330   0.8378   1.0000
   1.500   0.6098   0.02973   0.02245  -0.1355   0.8331   1.0000
   1.750   0.6305   0.03024   0.02287  -0.1346   0.8223   1.0000
   2.000   0.6750   0.03004   0.02257  -0.1371   0.8175   1.0000
   2.250   0.6960   0.03051   0.02298  -0.1361   0.8064   1.0000
   2.500   0.7418   0.03010   0.02250  -0.1386   0.8018   1.0000
   2.750   0.7636   0.03050   0.02287  -0.1376   0.7905   1.0000
   3.000   0.8106   0.02985   0.02220  -0.1400   0.7861   1.0000
   3.250   0.8332   0.03015   0.02249  -0.1391   0.7747   1.0000
   3.500   0.8825   0.02916   0.02150  -0.1415   0.7707   1.0000
   3.750   0.9364   0.02785   0.02022  -0.1445   0.7678   1.0000
   4.000   0.9603   0.02782   0.02022  -0.1434   0.7557   1.0000
   4.250   1.0219   0.02611   0.01855  -0.1476   0.7530   1.0000
   4.500   1.0452   0.02599   0.01850  -0.1461   0.7401   1.0000
   4.750   1.0805   0.02536   0.01792  -0.1464   0.7296   1.0000
   5.000   1.1385   0.02372   0.01636  -0.1501   0.7228   1.0000
   5.250   1.1700   0.02315   0.01584  -0.1497   0.7092   1.0000
   5.500   1.2050   0.02244   0.01519  -0.1498   0.6951   1.0000
   5.750   1.2401   0.02174   0.01456  -0.1500   0.6794   1.0000
   6.000   1.2744   0.02111   0.01394  -0.1500   0.6615   1.0000
   6.250   1.3053   0.02069   0.01352  -0.1496   0.6412   1.0000
   6.500   1.3260   0.02066   0.01353  -0.1476   0.6174   1.0000
   6.750   1.3508   0.02058   0.01342  -0.1463   0.5920   1.0000
   7.000   1.3732   0.02066   0.01341  -0.1446   0.5637   1.0000
   7.250   1.3899   0.02097   0.01364  -0.1421   0.5326   1.0000
   7.500   1.4035   0.02144   0.01402  -0.1391   0.4993   1.0000
   7.750   1.4137   0.02205   0.01451  -0.1357   0.4645   1.0000
   8.000   1.4211   0.02281   0.01510  -0.1319   0.4297   1.0000
   8.250   1.4269   0.02372   0.01583  -0.1279   0.3950   1.0000
   8.500   1.4316   0.02480   0.01671  -0.1240   0.3616   1.0000
   8.750   1.4357   0.02600   0.01772  -0.1203   0.3301   1.0000
   9.000   1.4400   0.02730   0.01885  -0.1167   0.3011   1.0000
   9.250   1.4455   0.02869   0.02007  -0.1135   0.2752   1.0000
   9.500   1.4516   0.03012   0.02136  -0.1105   0.2521   1.0000
   9.750   1.4597   0.03162   0.02271  -0.1080   0.2317   1.0000
  10.000   1.4685   0.03309   0.02414  -0.1056   0.2135   1.0000
  10.250   1.4787   0.03461   0.02560  -0.1035   0.1975   1.0000
  10.500   1.4904   0.03615   0.02710  -0.1016   0.1834   1.0000
  10.750   1.5035   0.03772   0.02863  -0.1000   0.1707   1.0000
  11.000   1.5193   0.03932   0.03012  -0.0988   0.1588   1.0000
  11.250   1.5297   0.04089   0.03184  -0.0968   0.1489   1.0000
  11.500   1.5446   0.04264   0.03366  -0.0955   0.1395   1.0000
  11.750   1.5661   0.04438   0.03529  -0.0951   0.1303   1.0000
  12.000   1.5733   0.04618   0.03736  -0.0929   0.1235   1.0000
  12.250   1.5952   0.04810   0.03922  -0.0926   0.1160   1.0000
  12.500   1.6006   0.05008   0.04149  -0.0903   0.1105   1.0000
  12.750   1.6261   0.05218   0.04349  -0.0905   0.1037   1.0000
  13.000   1.6247   0.05447   0.04617  -0.0877   0.0999   1.0000
  13.250   1.6311   0.05660   0.04845  -0.0859   0.0956   1.0000
  13.500   1.6489   0.05926   0.05114  -0.0855   0.0908   1.0000
  13.750   1.6411   0.06216   0.05444  -0.0826   0.0882   1.0000
  14.000   1.6388   0.06500   0.05755  -0.0805   0.0853   1.0000
  14.250   1.6467   0.06733   0.05992  -0.0794   0.0819   1.0000
  14.500   1.6491   0.07113   0.06392  -0.0781   0.0792   1.0000
  14.750   1.6297   0.07518   0.06837  -0.0757   0.0782   1.0000
  15.000   1.6098   0.07970   0.07328  -0.0740   0.0772   1.0000
  15.250   1.5888   0.08465   0.07857  -0.0728   0.0763   1.0000
  15.500   1.5658   0.09008   0.08433  -0.0724   0.0756   1.0000
  15.750   1.5399   0.09616   0.09073  -0.0728   0.0752   1.0000
  16.000   1.5094   0.10326   0.09814  -0.0743   0.0752   1.0000
  16.250   1.4737   0.11179   0.10696  -0.0774   0.0757   1.0000
  16.500   1.4326   0.12222   0.11767  -0.0826   0.0767   1.0000
  16.750   1.3888   0.13459   0.13025  -0.0899   0.0780   1.0000
  17.000   1.3454   0.14878   0.14458  -0.0992   0.0793   1.0000
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