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GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il)
Reynolds number: 100,000
Max Cl/Cd: 56.98 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe274-il-100000-n5.txt
Download as CSV file: xf-goe274-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 274 (DAIMLER V) AIRFOIL                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3266   0.10840   0.10354  -0.0274   1.0000   0.0387
  -8.250  -0.3387   0.10752   0.10276  -0.0265   1.0000   0.0390
  -8.000  -0.3506   0.10642   0.10176  -0.0257   1.0000   0.0391
  -7.750  -0.3554   0.10452   0.09993  -0.0272   1.0000   0.0392
  -7.500  -0.3562   0.10215   0.09760  -0.0291   1.0000   0.0393
  -7.250  -0.3547   0.09892   0.09443  -0.0299   1.0000   0.0395
  -7.000  -0.3532   0.09457   0.09011  -0.0245   1.0000   0.0401
  -6.750  -0.3513   0.09158   0.08717  -0.0223   1.0000   0.0407
  -6.500  -0.3496   0.08889   0.08452  -0.0215   1.0000   0.0414
  -6.250  -0.3469   0.08624   0.08190  -0.0216   1.0000   0.0423
  -6.000  -0.3413   0.08346   0.07914  -0.0225   0.9998   0.0438
  -5.750  -0.2969   0.07843   0.07396  -0.0365   0.9941   0.0484
  -5.500  -0.2461   0.07260   0.06785  -0.0512   0.9877   0.0494
  -5.250  -0.2280   0.06813   0.06344  -0.0514   0.9834   0.0506
  -5.000  -0.1982   0.06425   0.05950  -0.0554   0.9775   0.0527
  -4.750  -0.1345   0.05971   0.05443  -0.0701   0.9711   0.0599
  -4.500  -0.1138   0.05544   0.05030  -0.0711   0.9657   0.0617
  -4.000  -0.0292   0.04830   0.04262  -0.0832   0.9535   0.0728
  -3.750   0.0032   0.04504   0.03939  -0.0863   0.9495   0.0765
  -3.500   0.0392   0.04244   0.03651  -0.0901   0.9421   0.0882
  -3.250   0.0797   0.04010   0.03389  -0.0944   0.9369   0.1025
  -3.000   0.1135   0.03745   0.03125  -0.0970   0.9320   0.1102
  -2.750   0.1468   0.03533   0.02898  -0.0994   0.9241   0.1255
  -2.500   0.1871   0.03303   0.02653  -0.1034   0.9196   0.1517
  -2.000   0.2807   0.02835   0.02047  -0.1071   0.9056   0.0703
  -1.750   0.3143   0.02612   0.01807  -0.1083   0.8964   0.0634
  -1.500   0.3546   0.02467   0.01623  -0.1099   0.8891   0.0574
  -1.250   0.3861   0.02337   0.01475  -0.1103   0.8771   0.0555
  -1.000   0.4191   0.02223   0.01340  -0.1109   0.8649   0.0540
  -0.750   0.4526   0.02120   0.01217  -0.1114   0.8513   0.0529
  -0.500   0.4857   0.02034   0.01118  -0.1120   0.8360   0.0543
  -0.250   0.5191   0.01955   0.01026  -0.1125   0.8187   0.0560
   0.000   0.5529   0.01875   0.00934  -0.1131   0.7987   0.0559
   0.250   0.5845   0.01808   0.00858  -0.1132   0.7736   0.0557
   0.500   0.6163   0.01750   0.00789  -0.1134   0.7439   0.0557
   0.750   0.6467   0.01706   0.00729  -0.1133   0.7082   0.0561
   1.000   0.6754   0.01681   0.00684  -0.1130   0.6675   0.0566
   1.250   0.7027   0.01674   0.00649  -0.1124   0.6254   0.0575
   1.500   0.7289   0.01684   0.00627  -0.1118   0.5884   0.0595
   1.750   0.7550   0.01692   0.00608  -0.1113   0.5575   0.0638
   2.000   0.7810   0.01713   0.00603  -0.1108   0.5320   0.0670
   2.250   0.8070   0.01736   0.00605  -0.1103   0.5108   0.0697
   2.500   0.8333   0.01757   0.00612  -0.1099   0.4934   0.0745
   2.750   0.8600   0.01773   0.00628  -0.1097   0.4790   0.0946
   3.000   0.8774   0.01623   0.00647  -0.1075   0.4675   1.0000
   3.250   0.9036   0.01658   0.00665  -0.1071   0.4554   1.0000
   3.500   0.9296   0.01693   0.00686  -0.1068   0.4435   1.0000
   3.750   0.9556   0.01725   0.00711  -0.1064   0.4313   1.0000
   4.000   0.9813   0.01760   0.00738  -0.1061   0.4194   1.0000
   4.250   1.0067   0.01796   0.00766  -0.1057   0.4078   1.0000
   4.750   1.0570   0.01868   0.00832  -0.1048   0.3840   1.0000
   5.000   1.0819   0.01905   0.00869  -0.1044   0.3723   1.0000
   5.250   1.1066   0.01945   0.00906  -0.1039   0.3613   1.0000
   5.500   1.1307   0.01987   0.00948  -0.1033   0.3502   1.0000
   5.750   1.1549   0.02027   0.00991  -0.1027   0.3378   1.0000
   6.000   1.1787   0.02071   0.01037  -0.1021   0.3257   1.0000
   6.250   1.2020   0.02117   0.01086  -0.1014   0.3140   1.0000
   6.500   1.2247   0.02167   0.01134  -0.1007   0.3029   1.0000
   6.750   1.2475   0.02215   0.01189  -0.0999   0.2910   1.0000
   7.000   1.2700   0.02267   0.01245  -0.0991   0.2798   1.0000
   7.250   1.2919   0.02322   0.01305  -0.0983   0.2699   1.0000
   7.500   1.3137   0.02379   0.01368  -0.0974   0.2612   1.0000
   7.750   1.3353   0.02436   0.01435  -0.0965   0.2521   1.0000
   8.000   1.3551   0.02494   0.01495  -0.0954   0.2402   1.0000
   8.250   1.3737   0.02553   0.01560  -0.0941   0.2268   1.0000
   8.750   1.4101   0.02685   0.01704  -0.0915   0.2046   1.0000
   9.000   1.4267   0.02757   0.01782  -0.0900   0.1915   1.0000
   9.250   1.4431   0.02832   0.01870  -0.0884   0.1805   1.0000
   9.500   1.4574   0.02917   0.01960  -0.0866   0.1668   1.0000
   9.750   1.4707   0.03006   0.02056  -0.0847   0.1499   1.0000
  10.000   1.4845   0.03094   0.02155  -0.0828   0.1311   1.0000
  10.250   1.4828   0.03273   0.02295  -0.0790   0.0850   1.0000
  10.750   1.4696   0.03773   0.02763  -0.0712   0.0331   1.0000
  11.000   1.4675   0.03998   0.03000  -0.0682   0.0297   1.0000
  11.250   1.4644   0.04239   0.03258  -0.0655   0.0279   1.0000
  11.500   1.4596   0.04507   0.03543  -0.0630   0.0267   1.0000
  11.750   1.4564   0.04775   0.03835  -0.0611   0.0259   1.0000
  12.000   1.4505   0.05086   0.04169  -0.0596   0.0252   1.0000
  12.250   1.4425   0.05445   0.04551  -0.0586   0.0246   1.0000
  12.500   1.4320   0.05862   0.04992  -0.0583   0.0241   1.0000
  12.750   1.4192   0.06347   0.05499  -0.0587   0.0236   1.0000
  13.000   1.4044   0.06906   0.06081  -0.0600   0.0233   1.0000
  13.250   1.3878   0.07536   0.06734  -0.0620   0.0231   1.0000
  13.500   1.3700   0.08228   0.07447  -0.0646   0.0230   1.0000
  13.750   1.3514   0.08955   0.08194  -0.0675   0.0229   1.0000
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