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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 200,000
Max Cl/Cd: 75.29 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe174-il-200000.txt
Download as CSV file: xf-goe174-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 174 (ALBATROS 5020) AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2914   0.08970   0.08654  -0.0240   1.0000   0.0334
  -7.000  -0.2962   0.08780   0.08473  -0.0235   1.0000   0.0344
  -6.750  -0.3059   0.08650   0.08352  -0.0230   1.0000   0.0352
  -6.500  -0.3128   0.08527   0.08235  -0.0259   0.9994   0.0359
  -6.250  -0.2697   0.07806   0.07507  -0.0412   0.9932   0.0367
  -6.000  -0.2528   0.07403   0.07106  -0.0404   0.9890   0.0376
  -5.750  -0.2218   0.07003   0.06702  -0.0452   0.9845   0.0393
  -5.500  -0.1857   0.06552   0.06246  -0.0531   0.9765   0.0420
  -5.250  -0.1231   0.05773   0.05441  -0.0721   0.9678   0.0464
  -5.000  -0.1012   0.05503   0.05178  -0.0721   0.9618   0.0486
  -4.750  -0.0610   0.05123   0.04787  -0.0786   0.9535   0.0537
  -4.500  -0.0080   0.04518   0.04157  -0.0894   0.9469   0.0592
  -4.250   0.0266   0.04246   0.03880  -0.0925   0.9358   0.0638
  -4.000   0.0742   0.03784   0.03388  -0.0998   0.9241   0.0730
  -3.750   0.1203   0.03450   0.03014  -0.1054   0.9114   0.0858
  -3.500   0.1504   0.03232   0.02800  -0.1069   0.8969   0.0900
  -3.250   0.1861   0.02977   0.02514  -0.1096   0.8803   0.1027
  -3.000   0.2169   0.02802   0.02312  -0.1109   0.8620   0.1169
  -2.750   0.2439   0.02668   0.02160  -0.1112   0.8434   0.1320
  -2.500   0.2703   0.02541   0.02015  -0.1112   0.8253   0.1469
  -1.750   0.3707   0.01717   0.00978  -0.1108   0.7764   0.0706
  -1.500   0.3981   0.01592   0.00833  -0.1103   0.7600   0.0679
  -1.250   0.4256   0.01498   0.00717  -0.1098   0.7440   0.0659
  -1.000   0.4529   0.01430   0.00631  -0.1092   0.7283   0.0649
  -0.750   0.4801   0.01377   0.00565  -0.1086   0.7132   0.0646
  -0.500   0.5070   0.01338   0.00515  -0.1081   0.6989   0.0655
  -0.250   0.5339   0.01313   0.00481  -0.1076   0.6849   0.0680
   0.000   0.5608   0.01291   0.00449  -0.1071   0.6713   0.0691
   0.250   0.5877   0.01274   0.00422  -0.1067   0.6579   0.0705
   0.500   0.6147   0.01262   0.00401  -0.1063   0.6448   0.0746
   0.750   0.6417   0.01259   0.00391  -0.1059   0.6315   0.0822
   1.000   0.6683   0.01228   0.00397  -0.1057   0.6184   0.2144
   1.250   0.6932   0.01071   0.00404  -0.1049   0.6053   1.0000
   1.500   0.7198   0.01091   0.00406  -0.1045   0.5916   1.0000
   1.750   0.7462   0.01111   0.00410  -0.1040   0.5774   1.0000
   2.000   0.7725   0.01130   0.00416  -0.1035   0.5630   1.0000
   2.250   0.7986   0.01148   0.00422  -0.1030   0.5475   1.0000
   2.500   0.8245   0.01165   0.00428  -0.1025   0.5310   1.0000
   2.750   0.8502   0.01182   0.00436  -0.1020   0.5139   1.0000
   3.000   0.8759   0.01202   0.00445  -0.1015   0.4971   1.0000
   3.250   0.9015   0.01225   0.00456  -0.1010   0.4813   1.0000
   3.500   0.9272   0.01251   0.00472  -0.1005   0.4671   1.0000
   3.750   0.9529   0.01279   0.00493  -0.1001   0.4543   1.0000
   4.000   0.9785   0.01310   0.00515  -0.0997   0.4427   1.0000
   4.500   1.0297   0.01371   0.00564  -0.0989   0.4209   1.0000
   4.750   1.0555   0.01406   0.00595  -0.0985   0.4122   1.0000
   5.000   1.0812   0.01440   0.00626  -0.0982   0.4042   1.0000
   5.250   1.1068   0.01474   0.00660  -0.0978   0.3960   1.0000
   5.750   1.1565   0.01536   0.00720  -0.0968   0.3763   1.0000
   6.000   1.1813   0.01571   0.00755  -0.0964   0.3676   1.0000
   6.250   1.2062   0.01605   0.00790  -0.0959   0.3601   1.0000
   6.500   1.2310   0.01642   0.00832  -0.0955   0.3530   1.0000
   6.750   1.2558   0.01676   0.00872  -0.0950   0.3462   1.0000
   7.000   1.2807   0.01720   0.00917  -0.0946   0.3404   1.0000
   7.250   1.3048   0.01751   0.00960  -0.0941   0.3331   1.0000
   7.500   1.3285   0.01790   0.01002  -0.0935   0.3251   1.0000
   7.750   1.3508   0.01816   0.01036  -0.0926   0.3146   1.0000
   8.000   1.3729   0.01843   0.01074  -0.0917   0.3035   1.0000
   8.250   1.3948   0.01876   0.01114  -0.0908   0.2933   1.0000
   8.500   1.4159   0.01909   0.01153  -0.0898   0.2819   1.0000
   8.750   1.4364   0.01938   0.01192  -0.0887   0.2680   1.0000
   9.000   1.4568   0.01967   0.01234  -0.0876   0.2506   1.0000
   9.250   1.4759   0.02008   0.01281  -0.0864   0.2278   1.0000
   9.500   1.4887   0.02098   0.01353  -0.0843   0.1786   1.0000
   9.750   1.4819   0.02357   0.01549  -0.0799   0.1023   1.0000
  10.000   1.4667   0.02649   0.01800  -0.0743   0.0531   1.0000
  10.250   1.4612   0.02856   0.02021  -0.0699   0.0444   1.0000
  10.500   1.4559   0.03071   0.02250  -0.0663   0.0401   1.0000
  10.750   1.4501   0.03310   0.02503  -0.0633   0.0376   1.0000
  11.000   1.4506   0.03519   0.02729  -0.0613   0.0353   1.0000
  11.250   1.4492   0.03763   0.02985  -0.0597   0.0332   1.0000
  11.500   1.4451   0.04051   0.03284  -0.0585   0.0317   1.0000
  11.750   1.4349   0.04424   0.03666  -0.0576   0.0306   1.0000
  12.000   1.4275   0.04790   0.04044  -0.0570   0.0296   1.0000
  12.250   1.4253   0.05112   0.04380  -0.0566   0.0288   1.0000
  12.500   1.4219   0.05453   0.04734  -0.0564   0.0280   1.0000
  12.750   1.4186   0.05794   0.05084  -0.0561   0.0273   1.0000
  13.000   1.4159   0.06125   0.05425  -0.0557   0.0266   1.0000
  13.250   1.4140   0.06444   0.05752  -0.0553   0.0260   1.0000
  13.500   1.4131   0.06748   0.06063  -0.0548   0.0254   1.0000
  13.750   1.4131   0.07036   0.06356  -0.0542   0.0248   1.0000
  14.000   1.4149   0.07291   0.06613  -0.0531   0.0241   1.0000
  14.250   1.4212   0.07474   0.06798  -0.0505   0.0232   1.0000
  14.500   1.4217   0.07790   0.07132  -0.0505   0.0228   1.0000
  14.750   1.4230   0.08096   0.07454  -0.0503   0.0223   1.0000
  15.000   1.4253   0.08393   0.07768  -0.0497   0.0220   1.0000
  15.250   1.4260   0.08723   0.08115  -0.0493   0.0218   1.0000
  15.500   1.4245   0.09092   0.08504  -0.0493   0.0216   1.0000
  15.750   1.4208   0.09504   0.08935  -0.0497   0.0215   1.0000
  16.000   1.4146   0.09963   0.09416  -0.0505   0.0215   1.0000
  16.250   1.4060   0.10473   0.09948  -0.0519   0.0215   1.0000
  16.500   1.3954   0.11028   0.10525  -0.0539   0.0215   1.0000
  16.750   1.3832   0.11626   0.11144  -0.0564   0.0216   1.0000
  17.000   1.3695   0.12271   0.11811  -0.0595   0.0218   1.0000
  17.250   1.3551   0.12958   0.12518  -0.0632   0.0219   1.0000
  17.500   1.3402   0.13680   0.13259  -0.0674   0.0221   1.0000
  17.750   1.3246   0.14448   0.14045  -0.0721   0.0223   1.0000
  18.000   1.3085   0.15257   0.14871  -0.0773   0.0225   1.0000
  18.250   1.2926   0.16097   0.15727  -0.0828   0.0228   1.0000
  18.500   1.2771   0.16960   0.16603  -0.0885   0.0231   1.0000
  18.750   1.2676   0.17704   0.17357  -0.0931   0.0234   1.0000
  19.000   0.8447   0.19822   0.19521  -0.0831   0.0367   1.0000
  19.250   0.8472   0.20102   0.19803  -0.0834   0.0382   1.0000
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