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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 500,000
Max Cl/Cd: 99.2 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe630-il-500000-n5.txt
Download as CSV file: xf-goe630-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0555   0.09761   0.09445  -0.1146   0.8439   0.0180
 -11.000   0.0688   0.09633   0.09309  -0.1151   0.8295   0.0183
 -10.750   0.0737   0.09340   0.09010  -0.1160   0.8166   0.0182
 -10.500   0.0838   0.09170   0.08834  -0.1165   0.8048   0.0185
 -10.250   0.0914   0.08961   0.08618  -0.1171   0.7936   0.0188
 -10.000   0.0989   0.08753   0.08405  -0.1176   0.7822   0.0193
  -9.750   0.1046   0.08507   0.08154  -0.1183   0.7729   0.0196
  -9.500   0.1061   0.08196   0.07838  -0.1192   0.7630   0.0209
  -9.250   0.1045   0.07838   0.07478  -0.1205   0.7557   0.0213
  -9.000   0.1176   0.07739   0.07375  -0.1204   0.7473   0.0216
  -8.750   0.1252   0.07545   0.07179  -0.1208   0.7410   0.0218
  -8.500   0.1311   0.07326   0.06959  -0.1213   0.7344   0.0219
  -8.250   0.1393   0.07165   0.06795  -0.1215   0.7280   0.0226
  -8.000   0.1443   0.06946   0.06576  -0.1219   0.7221   0.0230
  -7.750   0.1463   0.06707   0.06336  -0.1223   0.7160   0.0237
  -7.250   0.1440   0.06249   0.05878  -0.1223   0.7051   0.0239
  -7.000   0.1460   0.05938   0.05567  -0.1243   0.6996   0.0242
  -6.750   0.1435   0.05379   0.05002  -0.1296   0.6941   0.0250
  -6.500   0.1592   0.05243   0.04866  -0.1305   0.6887   0.0252
  -6.250   0.1757   0.05106   0.04727  -0.1314   0.6829   0.0256
  -6.000   0.1908   0.04868   0.04482  -0.1335   0.6773   0.0259
  -5.750   0.2068   0.04530   0.04139  -0.1367   0.6720   0.0261
  -5.500   0.2247   0.04177   0.03776  -0.1399   0.6657   0.0263
  -5.250   0.2441   0.03788   0.03373  -0.1431   0.6602   0.0266
  -5.000   0.2408   0.01728   0.01138  -0.1502   0.6586   0.0289
  -4.750   0.2643   0.01620   0.01012  -0.1498   0.6522   0.0293
  -4.500   0.2893   0.01577   0.00958  -0.1493   0.6456   0.0296
  -4.250   0.3147   0.01535   0.00905  -0.1490   0.6394   0.0300
  -4.000   0.3401   0.01491   0.00849  -0.1485   0.6321   0.0305
  -3.750   0.3649   0.01433   0.00774  -0.1480   0.6250   0.0309
  -3.500   0.3902   0.01378   0.00703  -0.1475   0.6170   0.0313
  -3.250   0.4152   0.01331   0.00639  -0.1469   0.6094   0.0318
  -3.000   0.4408   0.01289   0.00584  -0.1464   0.6010   0.0323
  -2.750   0.4658   0.01255   0.00536  -0.1457   0.5922   0.0328
  -2.500   0.4911   0.01227   0.00495  -0.1451   0.5820   0.0332
  -2.250   0.5162   0.01205   0.00463  -0.1445   0.5723   0.0336
  -2.000   0.5406   0.01179   0.00429  -0.1438   0.5623   0.0342
  -1.750   0.5661   0.01169   0.00416  -0.1433   0.5525   0.0350
  -1.500   0.5908   0.01163   0.00403  -0.1426   0.5425   0.0358
  -1.250   0.6155   0.01155   0.00388  -0.1419   0.5317   0.0366
  -1.000   0.6400   0.01146   0.00372  -0.1412   0.5209   0.0373
  -0.750   0.6642   0.01142   0.00360  -0.1404   0.5107   0.0381
  -0.500   0.6887   0.01139   0.00350  -0.1397   0.5006   0.0389
  -0.250   0.7128   0.01132   0.00340  -0.1389   0.4919   0.0400
   0.000   0.7370   0.01133   0.00336  -0.1381   0.4827   0.0412
   0.250   0.7614   0.01134   0.00335  -0.1374   0.4744   0.0428
   0.500   0.7851   0.01141   0.00335  -0.1366   0.4654   0.0447
   0.750   0.8092   0.01141   0.00333  -0.1359   0.4574   0.0467
   1.000   0.8324   0.01148   0.00336  -0.1349   0.4488   0.0490
   1.250   0.8565   0.01153   0.00338  -0.1342   0.4418   0.0517
   1.500   0.8799   0.01159   0.00341  -0.1333   0.4347   0.0548
   1.750   0.9031   0.01167   0.00348  -0.1324   0.4286   0.0597
   2.000   0.9268   0.01173   0.00354  -0.1317   0.4225   0.0661
   2.250   0.9493   0.01182   0.00364  -0.1307   0.4165   0.0780
   2.500   0.9721   0.01186   0.00375  -0.1297   0.4111   0.1146
   2.750   0.9944   0.01185   0.00390  -0.1288   0.4054   0.1865
   3.000   1.0152   0.01189   0.00408  -0.1275   0.3999   0.2641
   3.250   1.0346   0.01168   0.00431  -0.1262   0.3950   0.4735
   3.750   1.1171   0.01133   0.00483  -0.1327   0.3837   1.0000
   4.000   1.1389   0.01153   0.00499  -0.1315   0.3799   1.0000
   4.250   1.1604   0.01170   0.00514  -0.1304   0.3757   1.0000
   4.500   1.1805   0.01190   0.00531  -0.1290   0.3717   1.0000
   4.750   1.1994   0.01213   0.00550  -0.1274   0.3677   1.0000
   5.000   1.2189   0.01236   0.00571  -0.1259   0.3641   1.0000
   5.250   1.2398   0.01256   0.00590  -0.1247   0.3606   1.0000
   5.500   1.2597   0.01279   0.00612  -0.1233   0.3566   1.0000
   5.750   1.2787   0.01305   0.00636  -0.1219   0.3528   1.0000
   6.000   1.2972   0.01335   0.00663  -0.1203   0.3496   1.0000
   6.250   1.3179   0.01358   0.00688  -0.1192   0.3469   1.0000
   6.500   1.3383   0.01383   0.00714  -0.1181   0.3440   1.0000
   6.750   1.3578   0.01411   0.00744  -0.1169   0.3409   1.0000
   7.000   1.3767   0.01443   0.00775  -0.1155   0.3380   1.0000
   7.250   1.3948   0.01478   0.00810  -0.1142   0.3353   1.0000
   7.500   1.4131   0.01515   0.00847  -0.1128   0.3326   1.0000
   7.750   1.4331   0.01544   0.00881  -0.1118   0.3302   1.0000
   8.000   1.4524   0.01578   0.00917  -0.1107   0.3274   1.0000
   8.250   1.4709   0.01615   0.00957  -0.1095   0.3247   1.0000
   8.500   1.4887   0.01657   0.01002  -0.1083   0.3221   1.0000
   8.750   1.5057   0.01703   0.01049  -0.1069   0.3197   1.0000
   9.000   1.5220   0.01755   0.01102  -0.1056   0.3172   1.0000
   9.250   1.5412   0.01793   0.01146  -0.1046   0.3144   1.0000
   9.500   1.5588   0.01839   0.01198  -0.1035   0.3104   1.0000
   9.750   1.5739   0.01899   0.01258  -0.1021   0.3059   1.0000
  10.000   1.5873   0.01970   0.01329  -0.1006   0.3011   1.0000
  10.250   1.6045   0.02022   0.01387  -0.0996   0.2955   1.0000
  10.500   1.6191   0.02091   0.01459  -0.0983   0.2910   1.0000
  10.750   1.6309   0.02177   0.01545  -0.0968   0.2857   1.0000
  11.000   1.6466   0.02243   0.01617  -0.0958   0.2798   1.0000
  11.250   1.6587   0.02333   0.01709  -0.0945   0.2740   1.0000
  11.500   1.6711   0.02424   0.01804  -0.0932   0.2687   1.0000
  11.750   1.6832   0.02519   0.01903  -0.0920   0.2614   1.0000
  12.000   1.6924   0.02637   0.02022  -0.0906   0.2551   1.0000
  12.250   1.7030   0.02748   0.02136  -0.0893   0.2466   1.0000
  12.500   1.7080   0.02903   0.02291  -0.0877   0.2344   1.0000
  12.750   1.7104   0.03084   0.02469  -0.0861   0.2205   1.0000
  13.000   1.7056   0.03330   0.02707  -0.0840   0.2015   1.0000
  13.250   1.6952   0.03634   0.03001  -0.0818   0.1795   1.0000
  13.500   1.6824   0.03974   0.03332  -0.0798   0.1602   1.0000
  13.750   1.6668   0.04354   0.03705  -0.0778   0.1394   1.0000
  14.000   1.6530   0.04738   0.04085  -0.0762   0.1224   1.0000
  14.250   1.6254   0.05281   0.04617  -0.0745   0.0972   1.0000
  14.500   1.6045   0.05783   0.05116  -0.0734   0.0816   1.0000
  14.750   1.5900   0.06229   0.05564  -0.0727   0.0709   1.0000
  15.000   1.5694   0.06767   0.06102  -0.0722   0.0569   1.0000
  15.250   1.5414   0.07418   0.06749  -0.0719   0.0395   1.0000
  15.500   1.5236   0.07957   0.07291  -0.0720   0.0315   1.0000
  15.750   1.5070   0.08491   0.07831  -0.0722   0.0255   1.0000
  16.000   1.4960   0.08960   0.08307  -0.0725   0.0225   1.0000
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