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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 500,000
Max Cl/Cd: 103.66 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe630-il-500000.txt
Download as CSV file: xf-goe630-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 630 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0869   0.08973   0.08696  -0.1211   0.8850   0.0290
  -9.750   0.1086   0.08649   0.08362  -0.1214   0.8705   0.0293
  -9.500   0.1221   0.08424   0.08127  -0.1219   0.8547   0.0295
  -9.250   0.1335   0.08237   0.07931  -0.1222   0.8409   0.0301
  -9.000   0.1415   0.08041   0.07730  -0.1225   0.8286   0.0307
  -8.750   0.1486   0.07836   0.07520  -0.1229   0.8180   0.0313
  -8.500   0.1550   0.07622   0.07300  -0.1235   0.8086   0.0320
  -8.250   0.1428   0.07389   0.07066  -0.1260   0.7973   0.0334
  -8.000   0.1365   0.07137   0.06811  -0.1271   0.7886   0.0336
  -7.750   0.1430   0.06860   0.06534  -0.1265   0.7813   0.0338
  -7.500   0.1584   0.06672   0.06339  -0.1255   0.7750   0.0341
  -7.250   0.1649   0.06495   0.06163  -0.1248   0.7681   0.0343
  -7.000   0.1712   0.06340   0.06005  -0.1243   0.7612   0.0347
  -6.750   0.1795   0.06158   0.05821  -0.1248   0.7548   0.0354
  -6.500   0.1875   0.05946   0.05609  -0.1259   0.7483   0.0363
  -6.250   0.1969   0.05707   0.05364  -0.1280   0.7422   0.0373
  -6.000   0.2074   0.05049   0.04695  -0.1393   0.7361   0.0390
  -5.750   0.2198   0.04868   0.04513  -0.1383   0.7299   0.0393
  -5.500   0.2357   0.04704   0.04342  -0.1383   0.7244   0.0397
  -5.250   0.2526   0.04544   0.04182  -0.1386   0.7185   0.0402
  -5.000   0.2712   0.04351   0.03984  -0.1397   0.7126   0.0411
  -4.750   0.3048   0.03696   0.03282  -0.1483   0.7077   0.0450
  -4.500   0.3187   0.03410   0.02999  -0.1482   0.7021   0.0456
  -4.250   0.3386   0.03283   0.02869  -0.1481   0.6960   0.0460
  -3.750   0.3823   0.03002   0.02572  -0.1483   0.6841   0.0478
  -3.500   0.4073   0.02521   0.02031  -0.1497   0.6787   0.0530
  -3.250   0.4297   0.02404   0.01911  -0.1495   0.6729   0.0537
  -3.000   0.4527   0.02304   0.01809  -0.1491   0.6659   0.0545
  -2.750   0.4763   0.02203   0.01695  -0.1488   0.6591   0.0559
  -2.500   0.4972   0.01624   0.00997  -0.1470   0.6539   0.0453
  -2.250   0.5215   0.01512   0.00866  -0.1463   0.6466   0.0454
  -2.000   0.5464   0.01431   0.00763  -0.1456   0.6398   0.0454
  -1.750   0.5713   0.01344   0.00666  -0.1450   0.6317   0.0458
  -1.500   0.5961   0.01288   0.00596  -0.1443   0.6239   0.0462
  -1.250   0.6214   0.01246   0.00550  -0.1437   0.6146   0.0470
  -1.000   0.6464   0.01215   0.00510  -0.1430   0.6058   0.0478
  -0.750   0.6715   0.01191   0.00480  -0.1424   0.5959   0.0490
  -0.500   0.6965   0.01172   0.00454  -0.1417   0.5863   0.0506
  -0.250   0.7210   0.01161   0.00433  -0.1408   0.5762   0.0518
   0.000   0.7452   0.01127   0.00395  -0.1400   0.5657   0.0532
   0.250   0.7688   0.01109   0.00373  -0.1391   0.5551   0.0551
   0.500   0.7922   0.01105   0.00363  -0.1382   0.5439   0.0573
   0.750   0.8163   0.01102   0.00356  -0.1374   0.5327   0.0600
   1.000   0.8394   0.01093   0.00343  -0.1364   0.5224   0.0638
   1.250   0.8624   0.01096   0.00341  -0.1354   0.5120   0.0681
   1.500   0.8862   0.01096   0.00338  -0.1346   0.5022   0.0735
   1.750   0.9088   0.01103   0.00342  -0.1335   0.4929   0.0829
   2.000   0.9319   0.01099   0.00347  -0.1326   0.4837   0.1168
   2.250   0.9521   0.01074   0.00368  -0.1313   0.4753   0.3246
   2.500   1.0112   0.00983   0.00404  -0.1387   0.4644   1.0000
   2.750   1.0343   0.01002   0.00414  -0.1378   0.4566   1.0000
   3.000   1.0566   0.01023   0.00427  -0.1367   0.4490   1.0000
   3.250   1.0792   0.01044   0.00441  -0.1357   0.4423   1.0000
   3.500   1.1019   0.01063   0.00455  -0.1348   0.4356   1.0000
   3.750   1.1228   0.01091   0.00472  -0.1335   0.4294   1.0000
   4.000   1.1461   0.01107   0.00488  -0.1327   0.4237   1.0000
   4.250   1.1678   0.01129   0.00505  -0.1316   0.4180   1.0000
   4.500   1.1883   0.01158   0.00526  -0.1303   0.4126   1.0000
   4.750   1.2110   0.01175   0.00544  -0.1293   0.4077   1.0000
   5.000   1.2317   0.01198   0.00563  -0.1281   0.4024   1.0000
   5.250   1.2502   0.01228   0.00586  -0.1264   0.3976   1.0000
   5.500   1.2709   0.01248   0.00607  -0.1251   0.3936   1.0000
   5.750   1.2910   0.01269   0.00629  -0.1238   0.3894   1.0000
   6.000   1.3100   0.01296   0.00653  -0.1223   0.3853   1.0000
   6.250   1.3287   0.01331   0.00682  -0.1208   0.3813   1.0000
   6.500   1.3492   0.01353   0.00708  -0.1196   0.3780   1.0000
   6.750   1.3694   0.01376   0.00734  -0.1184   0.3745   1.0000
   7.000   1.3888   0.01405   0.00762  -0.1170   0.3708   1.0000
   7.250   1.4075   0.01439   0.00794  -0.1156   0.3672   1.0000
   7.500   1.4273   0.01475   0.00829  -0.1145   0.3639   1.0000
   7.750   1.4473   0.01501   0.00861  -0.1133   0.3611   1.0000
   8.000   1.4669   0.01531   0.00894  -0.1122   0.3581   1.0000
   8.250   1.4861   0.01564   0.00929  -0.1110   0.3552   1.0000
   8.500   1.5048   0.01602   0.00967  -0.1098   0.3521   1.0000
   8.750   1.5246   0.01647   0.01009  -0.1088   0.3486   1.0000
   9.000   1.5414   0.01678   0.01049  -0.1073   0.3452   1.0000
   9.250   1.5584   0.01715   0.01091  -0.1059   0.3414   1.0000
   9.500   1.5744   0.01759   0.01136  -0.1044   0.3372   1.0000
   9.750   1.5902   0.01814   0.01188  -0.1030   0.3325   1.0000
  10.000   1.6069   0.01855   0.01239  -0.1017   0.3292   1.0000
  10.250   1.6220   0.01904   0.01294  -0.1002   0.3247   1.0000
  10.500   1.6362   0.01964   0.01354  -0.0987   0.3203   1.0000
  10.750   1.6503   0.02027   0.01420  -0.0973   0.3156   1.0000
  11.000   1.6653   0.02084   0.01486  -0.0960   0.3110   1.0000
  11.250   1.6782   0.02156   0.01562  -0.0946   0.3060   1.0000
  11.500   1.6906   0.02238   0.01642  -0.0931   0.3019   1.0000
  11.750   1.7056   0.02303   0.01721  -0.0920   0.2973   1.0000
  12.000   1.7175   0.02390   0.01811  -0.0907   0.2915   1.0000
  12.250   1.7270   0.02495   0.01918  -0.0892   0.2859   1.0000
  12.500   1.7400   0.02583   0.02015  -0.0881   0.2794   1.0000
  12.750   1.7460   0.02720   0.02152  -0.0865   0.2714   1.0000
  13.000   1.7546   0.02845   0.02283  -0.0852   0.2609   1.0000
  13.250   1.7609   0.02992   0.02432  -0.0838   0.2502   1.0000
  13.500   1.7600   0.03202   0.02638  -0.0821   0.2333   1.0000
  13.750   1.7507   0.03490   0.02918  -0.0799   0.2103   1.0000
  14.000   1.7318   0.03879   0.03291  -0.0775   0.1824   1.0000
  14.250   1.7079   0.04334   0.03732  -0.0752   0.1563   1.0000
  14.500   1.6829   0.04828   0.04216  -0.0732   0.1326   1.0000
  14.750   1.6569   0.05358   0.04737  -0.0717   0.1093   1.0000
  15.000   1.6280   0.05951   0.05323  -0.0705   0.0887   1.0000
  15.250   1.6024   0.06535   0.05905  -0.0698   0.0734   1.0000
  15.500   1.5773   0.07137   0.06507  -0.0695   0.0581   1.0000
  15.750   1.5510   0.07776   0.07143  -0.0695   0.0434   1.0000
  16.000   1.5258   0.08421   0.07790  -0.0697   0.0345   1.0000
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