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GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 392 AIRFOIL (goe392-il)
Reynolds number: 100,000
Max Cl/Cd: 58.08 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe392-il-100000-n5.txt
Download as CSV file: xf-goe392-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 392 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3096   0.10779   0.10346  -0.0415   1.0000   0.0316
  -8.250  -0.3169   0.10598   0.10175  -0.0405   1.0000   0.0317
  -8.000  -0.3268   0.10451   0.10038  -0.0388   1.0000   0.0317
  -7.750  -0.3160   0.10068   0.09659  -0.0441   0.9942   0.0319
  -7.500  -0.2998   0.09616   0.09208  -0.0511   0.9855   0.0319
  -7.250  -0.2844   0.09050   0.08645  -0.0539   0.9797   0.0324
  -7.000  -0.2688   0.08624   0.08217  -0.0550   0.9732   0.0334
  -6.750  -0.2506   0.08178   0.07770  -0.0597   0.9643   0.0342
  -6.500  -0.2293   0.07710   0.07297  -0.0659   0.9562   0.0357
  -6.000  -0.1876   0.06737   0.06315  -0.0808   0.9337   0.0398
  -5.750  -0.1508   0.06101   0.05631  -0.0959   0.9212   0.0419
  -5.500  -0.1407   0.05706   0.05267  -0.0933   0.9173   0.0459
  -5.250  -0.1079   0.05206   0.04714  -0.1026   0.9063   0.0541
  -5.000  -0.0842   0.04706   0.04218  -0.1054   0.9020   0.0580
  -4.500  -0.0148   0.03587   0.02973  -0.1112   0.8873   0.0208
  -4.250   0.0114   0.03238   0.02580  -0.1124   0.8787   0.0203
  -4.000   0.0447   0.02916   0.02203  -0.1142   0.8732   0.0200
  -3.750   0.0741   0.02666   0.01900  -0.1147   0.8652   0.0201
  -3.250   0.1381   0.02248   0.01388  -0.1162   0.8515   0.0240
  -3.000   0.1716   0.02077   0.01188  -0.1170   0.8454   0.0256
  -2.750   0.2015   0.01947   0.01039  -0.1170   0.8375   0.0281
  -2.500   0.2317   0.01834   0.00909  -0.1173   0.8300   0.0342
  -2.250   0.2620   0.01745   0.00799  -0.1177   0.8222   0.0409
  -2.000   0.2906   0.01666   0.00699  -0.1178   0.8136   0.0547
  -1.750   0.3207   0.01508   0.00635  -0.1188   0.8065   0.2946
  -1.500   0.3466   0.01471   0.00618  -0.1184   0.7969   0.4482
  -1.250   0.3735   0.01411   0.00599  -0.1181   0.7889   0.5768
  -1.000   0.3986   0.01346   0.00586  -0.1167   0.7801   0.7848
  -0.750   0.4509   0.01322   0.00546  -0.1217   0.7715   1.0000
  -0.500   0.4807   0.01328   0.00524  -0.1221   0.7628   1.0000
  -0.250   0.5066   0.01340   0.00515  -0.1218   0.7521   1.0000
   0.000   0.5328   0.01351   0.00507  -0.1215   0.7417   1.0000
   0.250   0.5599   0.01361   0.00498  -0.1214   0.7316   1.0000
   0.500   0.5871   0.01371   0.00491  -0.1213   0.7214   1.0000
   0.750   0.6120   0.01384   0.00494  -0.1208   0.7100   1.0000
   1.000   0.6374   0.01397   0.00496  -0.1204   0.6993   1.0000
   1.250   0.6638   0.01410   0.00499  -0.1201   0.6895   1.0000
   1.500   0.6897   0.01424   0.00505  -0.1198   0.6797   1.0000
   1.750   0.7145   0.01441   0.00520  -0.1193   0.6693   1.0000
   2.000   0.7402   0.01457   0.00531  -0.1189   0.6598   1.0000
   2.250   0.7663   0.01472   0.00543  -0.1187   0.6506   1.0000
   2.500   0.7907   0.01492   0.00568  -0.1181   0.6403   1.0000
   2.750   0.8160   0.01511   0.00589  -0.1177   0.6309   1.0000
   3.000   0.8419   0.01530   0.00609  -0.1174   0.6220   1.0000
   3.250   0.8660   0.01552   0.00640  -0.1168   0.6119   1.0000
   3.500   0.8911   0.01575   0.00674  -0.1163   0.6025   1.0000
   3.750   0.9154   0.01595   0.00701  -0.1156   0.5905   1.0000
   4.000   0.9299   0.01601   0.00690  -0.1125   0.5476   1.0000
   4.250   0.9418   0.01633   0.00696  -0.1091   0.4928   1.0000
   4.500   0.9494   0.01703   0.00721  -0.1052   0.4071   1.0000
   5.000   0.9364   0.02179   0.00975  -0.0946   0.0337   1.0000
   5.250   0.9518   0.02270   0.01079  -0.0924   0.0252   1.0000
   5.500   0.9658   0.02367   0.01198  -0.0901   0.0227   1.0000
   5.750   0.9794   0.02455   0.01311  -0.0877   0.0215   1.0000
   6.000   0.9898   0.02555   0.01433  -0.0848   0.0195   1.0000
   6.250   0.9958   0.02679   0.01576  -0.0815   0.0176   1.0000
   6.500   0.9984   0.02821   0.01736  -0.0779   0.0169   1.0000
   6.750   0.9968   0.02988   0.01927  -0.0740   0.0165   1.0000
   7.000   0.9940   0.03171   0.02122  -0.0703   0.0162   1.0000
   7.250   0.9922   0.03366   0.02323  -0.0669   0.0160   1.0000
   7.500   0.9971   0.03565   0.02518  -0.0642   0.0158   1.0000
   7.750   1.0172   0.03715   0.02664  -0.0628   0.0155   1.0000
   8.000   1.0383   0.03841   0.02804  -0.0617   0.0148   1.0000
   8.250   1.0658   0.03988   0.02966  -0.0610   0.0139   1.0000
   8.500   1.1184   0.04241   0.03228  -0.0630   0.0140   1.0000
   8.750   1.1783   0.04647   0.03653  -0.0671   0.0147   1.0000
   9.000   1.2240   0.05014   0.04050  -0.0693   0.0167   1.0000
   9.250   1.2379   0.05206   0.04300  -0.0659   0.0199   1.0000
  17.250   1.0197   0.21783   0.21321  -0.1045   0.0363   1.0000
  18.750   0.8055   0.22400   0.22022  -0.1002   0.0375   1.0000
  19.000   0.8062   0.22794   0.22417  -0.1024   0.0346   1.0000
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