Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 775 AIRFOIL (goe775-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 775 AIRFOIL (goe775-il)
Reynolds number: 200,000
Max Cl/Cd: 43.4 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe775-il-200000-n5.txt
Download as CSV file: xf-goe775-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 775 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -1.0841   0.10448   0.09806  -0.0346   1.0000   0.0731
 -19.000  -1.0886   0.10042   0.09392  -0.0363   1.0000   0.0746
 -18.750  -1.0933   0.09637   0.08975  -0.0380   1.0000   0.0762
 -18.500  -1.0958   0.09273   0.08605  -0.0394   1.0000   0.0776
 -18.250  -1.0986   0.08908   0.08237  -0.0408   1.0000   0.0790
 -18.000  -1.1015   0.08541   0.07864  -0.0421   1.0000   0.0806
 -17.750  -1.1039   0.08186   0.07499  -0.0434   1.0000   0.0823
 -17.500  -1.1054   0.07844   0.07145  -0.0445   1.0000   0.0841
 -17.250  -1.1065   0.07520   0.06819  -0.0455   1.0000   0.0856
 -17.000  -1.1080   0.07191   0.06486  -0.0464   1.0000   0.0872
 -16.750  -1.1088   0.06874   0.06162  -0.0473   1.0000   0.0891
 -16.500  -1.1080   0.06581   0.05858  -0.0480   1.0000   0.0911
 -16.250  -1.1070   0.06297   0.05568  -0.0487   1.0000   0.0930
 -16.000  -1.1075   0.06004   0.05272  -0.0493   1.0000   0.0948
 -15.750  -1.1064   0.05730   0.04992  -0.0497   1.0000   0.0969
 -15.500  -1.1034   0.05483   0.04737  -0.0501   1.0000   0.0992
 -15.250  -1.0999   0.05248   0.04494  -0.0503   1.0000   0.1014
 -15.000  -1.0988   0.04996   0.04240  -0.0504   1.0000   0.1034
 -14.750  -1.0959   0.04765   0.04005  -0.0505   1.0000   0.1057
 -14.500  -1.0907   0.04563   0.03795  -0.0504   1.0000   0.1083
 -14.250  -1.0851   0.04371   0.03596  -0.0502   1.0000   0.1107
 -14.000  -1.0823   0.04160   0.03386  -0.0498   1.0000   0.1130
 -13.750  -1.0775   0.03974   0.03195  -0.0494   1.0000   0.1157
 -13.500  -1.0701   0.03815   0.03029  -0.0489   1.0000   0.1187
 -13.250  -1.0640   0.03651   0.02862  -0.0482   1.0000   0.1214
 -13.000  -1.0590   0.03487   0.02697  -0.0473   1.0000   0.1243
 -12.750  -1.0518   0.03346   0.02553  -0.0464   1.0000   0.1276
 -12.500  -1.0426   0.03226   0.02426  -0.0454   1.0000   0.1310
 -12.250  -1.0378   0.03086   0.02289  -0.0440   1.0000   0.1341
 -12.000  -1.0308   0.02970   0.02171  -0.0425   1.0000   0.1378
 -11.750  -1.0218   0.02875   0.02072  -0.0409   1.0000   0.1417
 -11.500  -1.0173   0.02770   0.01968  -0.0387   1.0000   0.1453
 -11.250  -1.0123   0.02681   0.01879  -0.0363   1.0000   0.1494
 -11.000  -1.0064   0.02611   0.01806  -0.0337   1.0000   0.1537
 -10.750  -1.0055   0.02535   0.01733  -0.0304   1.0000   0.1576
 -10.500  -1.0049   0.02474   0.01672  -0.0267   1.0000   0.1620
 -10.250  -1.0039   0.02426   0.01621  -0.0228   1.0000   0.1664
 -10.000  -1.0088   0.02377   0.01574  -0.0179   1.0000   0.1703
  -9.750  -1.0068   0.02329   0.01526  -0.0142   0.9991   0.1753
  -9.500  -0.9801   0.02267   0.01463  -0.0150   0.9948   0.1826
  -9.250  -0.9536   0.02205   0.01403  -0.0159   0.9907   0.1906
  -9.000  -0.9285   0.02149   0.01347  -0.0162   0.9851   0.1983
  -8.750  -0.9008   0.02095   0.01294  -0.0170   0.9803   0.2068
  -8.500  -0.8734   0.02043   0.01244  -0.0177   0.9754   0.2148
  -8.250  -0.8479   0.01996   0.01198  -0.0178   0.9689   0.2232
  -8.000  -0.8171   0.01945   0.01149  -0.0190   0.9645   0.2316
  -7.750  -0.7917   0.01902   0.01107  -0.0189   0.9576   0.2402
  -7.500  -0.7640   0.01858   0.01065  -0.0193   0.9509   0.2484
  -7.250  -0.7317   0.01813   0.01021  -0.0205   0.9463   0.2580
  -7.000  -0.7103   0.01777   0.00988  -0.0195   0.9365   0.2659
  -6.750  -0.6804   0.01737   0.00949  -0.0201   0.9300   0.2756
  -6.500  -0.6571   0.01703   0.00918  -0.0193   0.9203   0.2839
  -6.250  -0.6297   0.01668   0.00883  -0.0193   0.9119   0.2937
  -6.000  -0.6062   0.01637   0.00854  -0.0185   0.9015   0.3026
  -5.750  -0.5801   0.01606   0.00823  -0.0181   0.8916   0.3127
  -5.500  -0.5576   0.01579   0.00799  -0.0170   0.8796   0.3218
  -5.250  -0.5315   0.01551   0.00770  -0.0166   0.8691   0.3323
  -5.000  -0.5097   0.01527   0.00749  -0.0153   0.8554   0.3417
  -4.750  -0.4847   0.01504   0.00724  -0.0146   0.8432   0.3528
  -4.500  -0.4615   0.01479   0.00702  -0.0136   0.8289   0.3640
  -4.250  -0.4377   0.01460   0.00682  -0.0127   0.8138   0.3765
  -4.000  -0.4138   0.01438   0.00661  -0.0118   0.7988   0.3891
  -3.750  -0.3885   0.01419   0.00639  -0.0111   0.7837   0.3998
  -3.500  -0.3637   0.01403   0.00621  -0.0103   0.7680   0.4107
  -3.250  -0.3387   0.01388   0.00604  -0.0096   0.7530   0.4207
  -3.000  -0.3134   0.01376   0.00587  -0.0089   0.7387   0.4313
  -2.750  -0.2883   0.01366   0.00574  -0.0082   0.7245   0.4413
  -2.500  -0.2633   0.01357   0.00563  -0.0075   0.7111   0.4525
  -2.000  -0.2130   0.01343   0.00545  -0.0062   0.6852   0.4742
  -1.750  -0.1878   0.01338   0.00537  -0.0055   0.6730   0.4851
  -1.500  -0.1627   0.01333   0.00532  -0.0048   0.6600   0.4972
  -1.250  -0.1377   0.01328   0.00527  -0.0041   0.6482   0.5085
  -1.000  -0.1123   0.01326   0.00522  -0.0035   0.6352   0.5206
  -0.750  -0.0874   0.01321   0.00520  -0.0027   0.6231   0.5324
  -0.500  -0.0622   0.01320   0.00517  -0.0020   0.6102   0.5448
  -0.250  -0.0373   0.01318   0.00516  -0.0013   0.5975   0.5578
   0.000  -0.0124   0.01318   0.00514  -0.0005   0.5847   0.5704
   0.250   0.0126   0.01318   0.00515   0.0002   0.5711   0.5840
   0.500   0.0375   0.01318   0.00516   0.0009   0.5586   0.5967
   0.750   0.0625   0.01320   0.00517   0.0016   0.5456   0.6096
   1.000   0.0876   0.01321   0.00520   0.0023   0.5333   0.6226
   1.250   0.1125   0.01326   0.00522   0.0031   0.5214   0.6346
   1.500   0.1379   0.01328   0.00527   0.0037   0.5093   0.6476
   1.750   0.1629   0.01333   0.00531   0.0044   0.4982   0.6595
   2.000   0.1881   0.01337   0.00537   0.0051   0.4861   0.6726
   2.250   0.2132   0.01343   0.00544   0.0058   0.4752   0.6848
   2.750   0.2635   0.01357   0.00562   0.0071   0.4536   0.7107
   3.000   0.2885   0.01365   0.00573   0.0078   0.4424   0.7242
   3.250   0.3136   0.01376   0.00587   0.0085   0.4323   0.7384
   3.500   0.3390   0.01387   0.00603   0.0092   0.4218   0.7528
   3.750   0.3639   0.01402   0.00620   0.0099   0.4118   0.7678
   4.000   0.3889   0.01418   0.00639   0.0107   0.4009   0.7835
   4.250   0.4140   0.01437   0.00661   0.0114   0.3903   0.7987
   4.500   0.4381   0.01458   0.00681   0.0123   0.3776   0.8137
   4.750   0.4619   0.01478   0.00701   0.0132   0.3653   0.8288
   5.000   0.4849   0.01503   0.00723   0.0142   0.3539   0.8432
   5.250   0.5101   0.01525   0.00748   0.0149   0.3429   0.8554
   5.500   0.5318   0.01550   0.00769   0.0162   0.3334   0.8692
   5.750   0.5580   0.01577   0.00797   0.0166   0.3229   0.8797
   6.000   0.5804   0.01605   0.00822   0.0177   0.3138   0.8916
   6.250   0.6066   0.01635   0.00853   0.0180   0.3038   0.9015
   6.500   0.6300   0.01666   0.00882   0.0188   0.2948   0.9120
   6.750   0.6576   0.01701   0.00916   0.0188   0.2849   0.9204
   7.000   0.6809   0.01735   0.00948   0.0196   0.2766   0.9301
   7.250   0.7110   0.01775   0.00986   0.0190   0.2669   0.9366
   7.500   0.7323   0.01811   0.01019   0.0200   0.2590   0.9464
   7.750   0.7648   0.01855   0.01063   0.0187   0.2493   0.9510
   8.000   0.7921   0.01901   0.01105   0.0185   0.2412   0.9578
   8.250   0.8181   0.01943   0.01147   0.0184   0.2325   0.9646
   8.500   0.8486   0.01994   0.01195   0.0172   0.2242   0.9691
   8.750   0.8744   0.02040   0.01241   0.0171   0.2157   0.9756
   9.000   0.9018   0.02092   0.01292   0.0164   0.2077   0.9805
   9.250   0.9299   0.02145   0.01343   0.0155   0.1992   0.9852
   9.500   0.9546   0.02202   0.01400   0.0152   0.1917   0.9909
   9.750   0.9817   0.02262   0.01459   0.0143   0.1836   0.9949
  10.000   1.0081   0.02325   0.01522   0.0135   0.1762   0.9992
  10.250   1.0092   0.02370   0.01568   0.0174   0.1713   1.0000
  10.750   1.0051   0.02468   0.01666   0.0262   0.1629   1.0000
  11.000   1.0063   0.02528   0.01726   0.0298   0.1585   1.0000
  11.500   1.0131   0.02675   0.01873   0.0358   0.1503   1.0000
  11.750   1.0186   0.02762   0.01960   0.0381   0.1461   1.0000
  12.250   1.0322   0.02963   0.02164   0.0418   0.1385   1.0000
  12.500   1.0396   0.03077   0.02279   0.0433   0.1348   1.0000
  12.750   1.0449   0.03214   0.02414   0.0447   0.1316   1.0000
  13.000   1.0536   0.03338   0.02543   0.0457   0.1283   1.0000
  13.250   1.0613   0.03476   0.02686   0.0466   0.1249   1.0000
  13.500   1.0667   0.03637   0.02848   0.0475   0.1220   1.0000
  13.750   1.0722   0.03805   0.03018   0.0481   0.1193   1.0000
  14.000   1.0800   0.03961   0.03182   0.0487   0.1163   1.0000
  14.250   1.0853   0.04144   0.03369   0.0491   0.1135   1.0000
  14.500   1.0885   0.04351   0.03577   0.0494   0.1112   1.0000
  14.750   1.0936   0.04548   0.03779   0.0496   0.1088   1.0000
  15.000   1.0992   0.04747   0.03986   0.0497   0.1062   1.0000
  15.250   1.1024   0.04974   0.04218   0.0496   0.1038   1.0000
  15.500   1.1039   0.05223   0.04469   0.0495   0.1018   1.0000
  15.750   1.1070   0.05462   0.04714   0.0493   0.0997   1.0000
  16.000   1.1103   0.05706   0.04967   0.0489   0.0974   1.0000
  16.250   1.1117   0.05976   0.05244   0.0485   0.0952   1.0000
  16.500   1.1116   0.06267   0.05537   0.0479   0.0934   1.0000
  16.750   1.1122   0.06554   0.05829   0.0472   0.0916   1.0000
  17.000   1.1133   0.06845   0.06131   0.0465   0.0895   1.0000
  17.250   1.1128   0.07158   0.06452   0.0456   0.0876   1.0000
  17.500   1.1116   0.07484   0.06783   0.0447   0.0859   1.0000
  17.750   1.1101   0.07812   0.07112   0.0437   0.0845   1.0000
  18.000   1.1089   0.08151   0.07463   0.0426   0.0827   1.0000
  18.250   1.1067   0.08504   0.07825   0.0413   0.0809   1.0000
  18.500   1.1037   0.08873   0.08202   0.0400   0.0793   1.0000
  18.750   1.1008   0.09241   0.08573   0.0386   0.0779   1.0000
  19.000   1.0985   0.09601   0.08938   0.0372   0.0765   1.0000
  19.250   1.0938   0.10008   0.09356   0.0355   0.0749   1.0000
<< Back to GOE 775 AIRFOIL (goe775-il)

Polar data table (+)

Polar graphs


<< Back to GOE 775 AIRFOIL (goe775-il)