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GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 430 AIRFOIL (goe430-il)
Reynolds number: 50,000
Max Cl/Cd: 30.71 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe430-il-50000.txt
Download as CSV file: xf-goe430-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 430 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2831   0.12054   0.11323  -0.0309   1.0000   0.2548
  -9.000  -0.3040   0.12121   0.11401  -0.0292   1.0000   0.2608
  -8.750  -0.3121   0.11936   0.11226  -0.0276   1.0000   0.2635
  -8.500  -0.2942   0.11543   0.10831  -0.0258   1.0000   0.2702
  -8.250  -0.3131   0.11566   0.10866  -0.0236   1.0000   0.2773
  -8.000  -0.3275   0.11451   0.10762  -0.0216   1.0000   0.2806
  -7.750  -0.3090   0.11071   0.10379  -0.0198   1.0000   0.2880
  -7.500  -0.3337   0.11130   0.10451  -0.0172   1.0000   0.2948
  -7.250  -0.3454   0.10967   0.10298  -0.0150   1.0000   0.2981
  -7.000  -0.3297   0.10620   0.09951  -0.0133   1.0000   0.3044
  -6.750  -0.3522   0.10631   0.09974  -0.0103   1.0000   0.3114
  -6.500  -0.3998   0.10819   0.10183  -0.0060   1.0000   0.3140
  -6.250  -0.3579   0.10210   0.09566  -0.0059   1.0000   0.3210
  -6.000  -0.3808   0.10200   0.09567  -0.0023   1.0000   0.3282
  -5.750  -0.4074   0.10147   0.09528  -0.0001   1.0000   0.3324
  -5.500  -0.3908   0.09827   0.09207   0.0024   1.0000   0.3408
  -5.250  -0.4267   0.09883   0.09280   0.0022   1.0000   0.3489
  -5.000  -0.4064   0.09499   0.08894   0.0062   1.0000   0.3559
  -4.000  -0.3590   0.06434   0.05765  -0.0482   1.0000   0.2271
  -3.750  -0.3303   0.05965   0.05279  -0.0546   1.0000   0.2242
  -3.500  -0.2820   0.05284   0.04551  -0.0676   1.0000   0.2220
  -3.250  -0.2284   0.04698   0.03899  -0.0798   1.0000   0.2243
  -3.000  -0.1943   0.04473   0.03643  -0.0844   1.0000   0.2330
  -2.750  -0.1551   0.04260   0.03378  -0.0901   0.9999   0.2461
  -2.500  -0.0965   0.04197   0.03306  -0.0970   0.9886   0.2663
  -2.250  -0.0384   0.04141   0.03220  -0.1041   0.9776   0.2972
  -2.000   0.0061   0.04168   0.03259  -0.1076   0.9663   0.3237
  -1.750   0.0522   0.04210   0.03302  -0.1116   0.9550   0.3551
  -1.500   0.0919   0.04225   0.03305  -0.1149   0.9425   0.3834
  -1.250   0.1281   0.04243   0.03325  -0.1171   0.9303   0.4031
  -1.000   0.1685   0.04266   0.03347  -0.1200   0.9188   0.4244
  -0.750   0.2171   0.04276   0.03344  -0.1246   0.9081   0.4520
  -0.500   0.2435   0.04310   0.03385  -0.1251   0.8956   0.4744
  -0.250   0.2790   0.04341   0.03416  -0.1272   0.8848   0.5059
   0.000   0.3170   0.04375   0.03460  -0.1289   0.8748   0.5440
   0.250   0.3374   0.04433   0.03524  -0.1282   0.8627   0.5777
   0.500   0.3678   0.04483   0.03579  -0.1287   0.8532   0.6179
   0.750   0.3935   0.04541   0.03638  -0.1289   0.8436   0.6593
   1.000   0.4132   0.04599   0.03704  -0.1281   0.8348   0.6980
   1.250   0.4381   0.04630   0.03742  -0.1279   0.8265   0.7449
   1.500   0.4519   0.04673   0.03800  -0.1261   0.8182   0.7940
   1.750   0.4609   0.04670   0.03824  -0.1227   0.8108   0.8682
   2.000   0.4870   0.04765   0.03915  -0.1252   0.8035   1.0000
   2.250   0.5162   0.04939   0.04068  -0.1289   0.7966   1.0000
   2.500   0.5646   0.05059   0.04163  -0.1338   0.7908   1.0000
   2.750   0.5675   0.05267   0.04362  -0.1329   0.7839   1.0000
   3.000   0.5884   0.05443   0.04527  -0.1340   0.7792   1.0000
   3.250   0.6283   0.05576   0.04647  -0.1368   0.7742   1.0000
   3.500   0.6242   0.05800   0.04867  -0.1349   0.7680   1.0000
   3.750   0.6662   0.05888   0.04946  -0.1371   0.7585   1.0000
   4.000   0.6672   0.06088   0.05144  -0.1354   0.7498   1.0000
   4.250   0.6982   0.06166   0.05217  -0.1358   0.7359   1.0000
   4.500   0.7313   0.06212   0.05259  -0.1361   0.7205   1.0000
   4.750   0.7695   0.06235   0.05280  -0.1367   0.7066   1.0000
   5.000   0.7894   0.06357   0.05403  -0.1362   0.6951   1.0000
   5.250   0.7995   0.06540   0.05588  -0.1351   0.6841   1.0000
   5.500   0.8317   0.06605   0.05656  -0.1353   0.6727   1.0000
   5.750   0.8651   0.06648   0.05704  -0.1354   0.6607   1.0000
   6.000   0.8757   0.06812   0.05874  -0.1341   0.6465   1.0000
   6.250   0.8947   0.06924   0.05992  -0.1330   0.6317   1.0000
   6.500   0.9170   0.07010   0.06086  -0.1320   0.6162   1.0000
   6.750   0.9413   0.07076   0.06160  -0.1309   0.6001   1.0000
   7.000   0.9678   0.07108   0.06200  -0.1297   0.5830   1.0000
   7.250   0.9954   0.07117   0.06220  -0.1283   0.5655   1.0000
   8.000   1.0734   0.07151   0.06285  -0.1235   0.5144   1.0000
   8.250   1.1854   0.06109   0.05264  -0.1217   0.5101   1.0000
   8.500   1.2848   0.05249   0.04418  -0.1215   0.4944   1.0000
   8.750   1.3381   0.04917   0.04091  -0.1207   0.4730   1.0000
   9.000   1.3707   0.04811   0.03989  -0.1191   0.4525   1.0000
   9.250   1.4076   0.04727   0.03907  -0.1183   0.4333   1.0000
   9.500   1.4377   0.04719   0.03899  -0.1172   0.4150   1.0000
   9.750   1.4614   0.04758   0.03940  -0.1157   0.3975   1.0000
  10.000   1.4772   0.04849   0.04035  -0.1136   0.3811   1.0000
  10.250   1.4861   0.04982   0.04178  -0.1109   0.3659   1.0000
  10.500   1.4915   0.05134   0.04338  -0.1080   0.3519   1.0000
  10.750   1.5011   0.05270   0.04480  -0.1054   0.3385   1.0000
  11.000   1.5191   0.05381   0.04593  -0.1037   0.3255   1.0000
  11.250   1.5473   0.05461   0.04674  -0.1030   0.3126   1.0000
  11.500   1.5118   0.05921   0.05161  -0.0977   0.3070   1.0000
  11.750   1.5397   0.06020   0.05264  -0.0970   0.2961   1.0000
  12.000   1.4851   0.06697   0.05970  -0.0923   0.2936   1.0000
  12.250   1.5303   0.06634   0.05905  -0.0919   0.2814   1.0000
  12.500   1.4570   0.07603   0.06902  -0.0886   0.2820   1.0000
  13.000   1.5958   0.06661   0.05904  -0.0872   0.2356   1.0000
  13.250   1.5567   0.07211   0.06489  -0.0836   0.2341   1.0000
  13.500   1.5107   0.07955   0.07265  -0.0815   0.2347   1.0000
  13.750   1.4589   0.08940   0.08272  -0.0815   0.2369   1.0000
  14.000   1.4769   0.08813   0.08143  -0.0791   0.2194   1.0000
  14.250   1.5466   0.08171   0.07467  -0.0761   0.1907   1.0000
  14.500   1.5024   0.08928   0.08257  -0.0755   0.1908   1.0000
  14.750   1.4615   0.09757   0.09108  -0.0763   0.1899   1.0000
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