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GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 384 AIRFOIL (goe384-il)
Reynolds number: 200,000
Max Cl/Cd: 59.08 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe384-il-200000-n5.txt
Download as CSV file: xf-goe384-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 384 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0219   0.09234   0.08733  -0.0900   0.7018   0.0441
 -10.000  -0.0217   0.08821   0.08318  -0.0923   0.6963   0.0440
  -9.750  -0.0225   0.08394   0.07887  -0.0947   0.6912   0.0440
  -9.500  -0.0251   0.07939   0.07428  -0.0975   0.6866   0.0440
  -9.250  -0.0300   0.07441   0.06926  -0.1008   0.6826   0.0442
  -9.000  -0.0410   0.06810   0.06295  -0.1058   0.6785   0.0447
  -8.750  -0.1642   0.04124   0.03533  -0.1255   0.6783   0.0453
  -8.500  -0.1885   0.03314   0.02623  -0.1247   0.6747   0.0464
  -8.250  -0.1761   0.03079   0.02346  -0.1240   0.6704   0.0470
  -7.750  -0.1317   0.02928   0.02174  -0.1234   0.6614   0.0480
  -7.500  -0.1093   0.02845   0.02078  -0.1231   0.6569   0.0487
  -7.250  -0.0875   0.02739   0.01950  -0.1227   0.6530   0.0495
  -7.000  -0.0658   0.02615   0.01796  -0.1223   0.6495   0.0504
  -6.750  -0.0434   0.02491   0.01638  -0.1219   0.6459   0.0512
  -6.500  -0.0201   0.02379   0.01495  -0.1214   0.6418   0.0521
  -6.250   0.0050   0.02310   0.01418  -0.1212   0.6376   0.0527
  -6.000   0.0309   0.02263   0.01366  -0.1211   0.6337   0.0535
  -5.750   0.0571   0.02222   0.01314  -0.1210   0.6303   0.0544
  -5.500   0.0835   0.02176   0.01255  -0.1209   0.6275   0.0556
  -5.250   0.1097   0.02121   0.01189  -0.1208   0.6243   0.0568
  -5.000   0.1360   0.02067   0.01120  -0.1206   0.6209   0.0579
  -4.750   0.1625   0.02019   0.01068  -0.1205   0.6176   0.0588
  -4.500   0.1892   0.01984   0.01032  -0.1204   0.6144   0.0598
  -4.250   0.2164   0.01956   0.00999  -0.1204   0.6116   0.0611
  -4.000   0.2440   0.01931   0.00963  -0.1204   0.6088   0.0627
  -3.750   0.2704   0.01899   0.00926  -0.1203   0.6055   0.0644
  -3.500   0.2967   0.01867   0.00897  -0.1201   0.6017   0.0657
  -3.250   0.3232   0.01843   0.00875  -0.1200   0.5980   0.0671
  -3.000   0.3501   0.01822   0.00851  -0.1199   0.5945   0.0689
  -2.750   0.3775   0.01804   0.00826  -0.1199   0.5914   0.0712
  -2.500   0.4044   0.01787   0.00808  -0.1198   0.5882   0.0733
  -2.250   0.4304   0.01771   0.00798  -0.1196   0.5841   0.0755
  -2.000   0.4566   0.01755   0.00783  -0.1194   0.5798   0.0781
  -1.750   0.4830   0.01740   0.00767  -0.1192   0.5756   0.0810
  -1.500   0.5102   0.01730   0.00753  -0.1192   0.5718   0.0847
  -1.250   0.5362   0.01721   0.00745  -0.1189   0.5674   0.0890
  -1.000   0.5617   0.01708   0.00739  -0.1187   0.5625   0.0934
  -0.750   0.5878   0.01698   0.00728  -0.1184   0.5578   0.0996
  -0.500   0.6143   0.01687   0.00713  -0.1183   0.5535   0.1074
  -0.250   0.6392   0.01676   0.00709  -0.1179   0.5478   0.1164
   0.000   0.6642   0.01665   0.00703  -0.1176   0.5416   0.1282
   0.250   0.6895   0.01650   0.00693  -0.1173   0.5363   0.1500
   0.500   0.7128   0.01618   0.00700  -0.1169   0.5297   0.2500
   0.750   0.7353   0.01580   0.00707  -0.1163   0.5231   0.3894
   1.250   0.7712   0.01482   0.00742  -0.1123   0.5093   0.8001
   1.500   0.8231   0.01485   0.00757  -0.1167   0.5003   0.9762
   1.750   0.8599   0.01502   0.00764  -0.1189   0.4906   1.0000
   2.000   0.8777   0.01518   0.00767  -0.1172   0.4828   1.0000
   2.250   0.8958   0.01536   0.00776  -0.1156   0.4749   1.0000
   2.500   0.9137   0.01558   0.00784  -0.1139   0.4681   1.0000
   2.750   0.9322   0.01582   0.00800  -0.1125   0.4611   1.0000
   3.000   0.9496   0.01609   0.00815  -0.1108   0.4547   1.0000
   3.250   0.9671   0.01637   0.00834  -0.1092   0.4488   1.0000
   3.500   0.9837   0.01667   0.00857  -0.1075   0.4429   1.0000
   3.750   1.0006   0.01702   0.00881  -0.1058   0.4378   1.0000
   4.000   1.0193   0.01736   0.00909  -0.1046   0.4333   1.0000
   4.250   1.0385   0.01771   0.00940  -0.1035   0.4289   1.0000
   4.500   1.0579   0.01809   0.00972  -0.1024   0.4247   1.0000
   4.750   1.0774   0.01849   0.01004  -0.1014   0.4210   1.0000
   5.000   1.0977   0.01890   0.01037  -0.1006   0.4175   1.0000
   5.250   1.1174   0.01931   0.01078  -0.0997   0.4137   1.0000
   5.500   1.1368   0.01974   0.01120  -0.0988   0.4099   1.0000
   5.750   1.1564   0.02019   0.01160  -0.0980   0.4064   1.0000
   6.000   1.1767   0.02064   0.01199  -0.0973   0.4033   1.0000
   6.250   1.1984   0.02108   0.01236  -0.0968   0.4006   1.0000
   6.500   1.2174   0.02157   0.01289  -0.0960   0.3978   1.0000
   6.750   1.2363   0.02207   0.01342  -0.0952   0.3949   1.0000
   7.000   1.2549   0.02260   0.01396  -0.0944   0.3919   1.0000
   7.250   1.2738   0.02313   0.01448  -0.0936   0.3890   1.0000
   7.500   1.2935   0.02365   0.01497  -0.0930   0.3862   1.0000
   7.750   1.3151   0.02413   0.01538  -0.0926   0.3835   1.0000
   8.000   1.3324   0.02475   0.01604  -0.0917   0.3811   1.0000
   8.250   1.3489   0.02541   0.01677  -0.0908   0.3785   1.0000
   8.500   1.3654   0.02608   0.01750  -0.0900   0.3760   1.0000
   8.750   1.3823   0.02676   0.01821  -0.0892   0.3734   1.0000
   9.000   1.3995   0.02742   0.01889  -0.0884   0.3710   1.0000
   9.250   1.4177   0.02805   0.01952  -0.0878   0.3686   1.0000
   9.500   1.4381   0.02859   0.02002  -0.0874   0.3663   1.0000
   9.750   1.4547   0.02933   0.02079  -0.0866   0.3639   1.0000
  10.000   1.4663   0.03030   0.02187  -0.0855   0.3614   1.0000
  10.250   1.4791   0.03125   0.02291  -0.0845   0.3590   1.0000
  10.500   1.4924   0.03219   0.02392  -0.0835   0.3566   1.0000
  10.750   1.5061   0.03312   0.02490  -0.0827   0.3543   1.0000
  11.000   1.5212   0.03396   0.02577  -0.0820   0.3520   1.0000
  11.250   1.5389   0.03464   0.02645  -0.0815   0.3498   1.0000
  11.500   1.5592   0.03521   0.02699  -0.0812   0.3475   1.0000
  11.750   1.5610   0.03690   0.02885  -0.0796   0.3447   1.0000
  12.000   1.5640   0.03858   0.03066  -0.0781   0.3412   1.0000
  12.250   1.5686   0.04018   0.03233  -0.0769   0.3373   1.0000
  12.500   1.5791   0.04135   0.03350  -0.0761   0.3336   1.0000
  12.750   1.5944   0.04218   0.03431  -0.0756   0.3304   1.0000
  13.000   1.5908   0.04469   0.03699  -0.0742   0.3268   1.0000
  13.250   1.5925   0.04682   0.03926  -0.0732   0.3234   1.0000
  13.500   1.5975   0.04870   0.04121  -0.0725   0.3203   1.0000
  13.750   1.6073   0.05013   0.04268  -0.0719   0.3176   1.0000
  14.000   1.6230   0.05099   0.04353  -0.0716   0.3152   1.0000
  14.250   1.6218   0.05359   0.04628  -0.0708   0.3121   1.0000
  14.500   1.6152   0.05680   0.04966  -0.0700   0.3082   1.0000
  14.750   1.6138   0.05951   0.05247  -0.0693   0.3045   1.0000
  15.000   1.6218   0.06120   0.05418  -0.0690   0.3012   1.0000
  15.250   1.6352   0.06229   0.05526  -0.0687   0.2982   1.0000
  15.500   1.6143   0.06733   0.06054  -0.0679   0.2934   1.0000
  15.750   1.6057   0.07103   0.06436  -0.0675   0.2888   1.0000
  16.000   1.6143   0.07268   0.06602  -0.0673   0.2851   1.0000
  16.250   1.6089   0.07607   0.06950  -0.0670   0.2808   1.0000
  16.500   1.5837   0.08201   0.07563  -0.0666   0.2752   1.0000
  16.750   1.5876   0.08434   0.07797  -0.0666   0.2705   1.0000
  17.000   1.5764   0.08862   0.08235  -0.0665   0.2653   1.0000
  17.250   1.5461   0.09556   0.08946  -0.0667   0.2588   1.0000
  17.500   1.5630   0.09619   0.09004  -0.0668   0.2542   1.0000
  17.750   1.5126   0.10617   0.10026  -0.0676   0.2465   1.0000
  18.000   1.5194   0.10821   0.10230  -0.0679   0.2410   1.0000
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