Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 619 AIRFOIL (goe619-il)
Reynolds number: 500,000
Max Cl/Cd: 99.66 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe619-il-500000.txt
Download as CSV file: xf-goe619-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 619 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6646   0.06736   0.06435  -0.0771   1.0000   0.0322
 -13.250  -0.7012   0.05908   0.05592  -0.0832   1.0000   0.0320
 -13.000  -0.7338   0.05219   0.04891  -0.0879   1.0000   0.0319
 -12.750  -0.7687   0.04595   0.04255  -0.0918   1.0000   0.0318
 -12.500  -0.8106   0.04224   0.03877  -0.0911   1.0000   0.0317
 -12.250  -0.8064   0.03860   0.03482  -0.0965   0.9948   0.0319
 -12.000  -0.7975   0.03345   0.02935  -0.1012   0.9884   0.0324
 -11.750  -0.7737   0.03099   0.02678  -0.1039   0.9847   0.0329
 -11.500  -0.7451   0.02912   0.02479  -0.1066   0.9823   0.0334
 -11.250  -0.7230   0.02762   0.02318  -0.1074   0.9763   0.0338
 -11.000  -0.6939   0.02624   0.02168  -0.1093   0.9728   0.0345
 -10.750  -0.6625   0.02486   0.02017  -0.1115   0.9705   0.0351
 -10.500  -0.6377   0.02363   0.01879  -0.1120   0.9650   0.0357
 -10.250  -0.6090   0.02242   0.01744  -0.1132   0.9608   0.0362
 -10.000  -0.5767   0.02131   0.01617  -0.1149   0.9582   0.0366
  -9.750  -0.5419   0.02034   0.01506  -0.1169   0.9563   0.0370
  -9.500  -0.5177   0.01900   0.01360  -0.1169   0.9497   0.0376
  -9.250  -0.4875   0.01778   0.01234  -0.1182   0.9453   0.0384
  -9.000  -0.4534   0.01692   0.01143  -0.1199   0.9420   0.0392
  -8.750  -0.4253   0.01621   0.01066  -0.1202   0.9349   0.0399
  -8.500  -0.3938   0.01551   0.00990  -0.1211   0.9288   0.0406
  -8.250  -0.3622   0.01489   0.00919  -0.1221   0.9225   0.0413
  -8.000  -0.3343   0.01436   0.00857  -0.1221   0.9139   0.0421
  -7.750  -0.3040   0.01388   0.00799  -0.1226   0.9066   0.0428
  -7.500  -0.2792   0.01326   0.00730  -0.1221   0.8969   0.0439
  -7.250  -0.2528   0.01277   0.00677  -0.1219   0.8880   0.0453
  -7.000  -0.2263   0.01240   0.00633  -0.1216   0.8788   0.0466
  -6.750  -0.2004   0.01208   0.00594  -0.1211   0.8700   0.0481
  -6.500  -0.1738   0.01177   0.00554  -0.1207   0.8613   0.0498
  -6.250  -0.1488   0.01141   0.00517  -0.1200   0.8521   0.0529
  -6.000  -0.1221   0.01114   0.00484  -0.1196   0.8436   0.0576
  -5.750  -0.0968   0.01086   0.00462  -0.1190   0.8348   0.0677
  -5.500  -0.0695   0.01071   0.00448  -0.1187   0.8266   0.0822
  -5.250  -0.0431   0.01061   0.00437  -0.1182   0.8179   0.0916
  -5.000  -0.0151   0.01062   0.00427  -0.1179   0.8099   0.0974
  -4.750   0.0106   0.01041   0.00408  -0.1174   0.8015   0.1035
  -4.500   0.0376   0.01033   0.00393  -0.1170   0.7935   0.1081
  -4.250   0.0644   0.01027   0.00380  -0.1166   0.7855   0.1115
  -4.000   0.0904   0.01007   0.00359  -0.1161   0.7774   0.1172
  -3.750   0.1171   0.00997   0.00346  -0.1156   0.7696   0.1221
  -3.500   0.1436   0.00987   0.00331  -0.1151   0.7613   0.1266
  -3.250   0.1699   0.00972   0.00316  -0.1147   0.7536   0.1337
  -3.000   0.1960   0.00962   0.00303  -0.1141   0.7447   0.1410
  -2.750   0.2219   0.00947   0.00290  -0.1135   0.7352   0.1523
  -2.500   0.2474   0.00935   0.00278  -0.1128   0.7242   0.1712
  -2.250   0.2726   0.00921   0.00273  -0.1121   0.7132   0.2000
  -2.000   0.2989   0.00916   0.00269  -0.1116   0.7046   0.2239
  -1.750   0.3254   0.00911   0.00268  -0.1111   0.6966   0.2423
  -1.250   0.3789   0.00909   0.00264  -0.1102   0.6814   0.2688
  -1.000   0.4054   0.00908   0.00262  -0.1098   0.6743   0.2801
  -0.750   0.4322   0.00907   0.00261  -0.1094   0.6672   0.2911
  -0.500   0.4587   0.00907   0.00261  -0.1089   0.6597   0.3019
  -0.250   0.4851   0.00906   0.00260  -0.1084   0.6524   0.3124
   0.000   0.5114   0.00906   0.00259  -0.1079   0.6441   0.3233
   0.250   0.5374   0.00905   0.00260  -0.1073   0.6362   0.3357
   0.500   0.5632   0.00903   0.00261  -0.1067   0.6272   0.3496
   0.750   0.5890   0.00904   0.00264  -0.1061   0.6193   0.3668
   1.000   0.6146   0.00902   0.00267  -0.1055   0.6102   0.3879
   1.250   0.6400   0.00902   0.00271  -0.1049   0.6014   0.4098
   1.500   0.6650   0.00901   0.00275  -0.1041   0.5916   0.4356
   1.750   0.6897   0.00898   0.00280  -0.1034   0.5815   0.4689
   2.000   0.7132   0.00893   0.00284  -0.1024   0.5705   0.5126
   2.250   0.7290   0.00838   0.00296  -0.0998   0.5585   0.7262
   2.500   0.8081   0.00818   0.00316  -0.1105   0.5369   1.0000
   2.750   0.8291   0.00833   0.00322  -0.1090   0.5190   1.0000
   3.000   0.8491   0.00852   0.00330  -0.1072   0.4971   1.0000
   3.250   0.8673   0.00878   0.00341  -0.1052   0.4719   1.0000
   3.500   0.8855   0.00907   0.00355  -0.1032   0.4444   1.0000
   3.750   0.9033   0.00940   0.00373  -0.1011   0.4189   1.0000
   4.000   0.9212   0.00975   0.00393  -0.0991   0.3938   1.0000
   4.250   0.9392   0.01010   0.00414  -0.0971   0.3721   1.0000
   4.500   0.9577   0.01044   0.00436  -0.0953   0.3515   1.0000
   4.750   0.9763   0.01078   0.00459  -0.0935   0.3334   1.0000
   5.000   0.9950   0.01111   0.00482  -0.0917   0.3181   1.0000
   5.250   1.0136   0.01143   0.00507  -0.0899   0.3061   1.0000
   5.500   1.0333   0.01171   0.00530  -0.0883   0.2958   1.0000
   5.750   1.0518   0.01200   0.00554  -0.0865   0.2871   1.0000
   6.000   1.0695   0.01229   0.00579  -0.0845   0.2793   1.0000
   6.250   1.0870   0.01258   0.00605  -0.0825   0.2728   1.0000
   6.500   1.1057   0.01284   0.00630  -0.0808   0.2663   1.0000
   6.750   1.1222   0.01320   0.00660  -0.0787   0.2601   1.0000
   7.000   1.1417   0.01345   0.00687  -0.0772   0.2550   1.0000
   7.250   1.1603   0.01374   0.00716  -0.0755   0.2501   1.0000
   7.500   1.1768   0.01413   0.00750  -0.0736   0.2444   1.0000
   7.750   1.1962   0.01440   0.00779  -0.0721   0.2386   1.0000
   8.000   1.2142   0.01473   0.00812  -0.0705   0.2328   1.0000
   8.250   1.2298   0.01518   0.00852  -0.0685   0.2269   1.0000
   8.500   1.2500   0.01544   0.00882  -0.0673   0.2218   1.0000
   8.750   1.2674   0.01582   0.00920  -0.0657   0.2166   1.0000
   9.000   1.2827   0.01630   0.00966  -0.0639   0.2112   1.0000
   9.250   1.3023   0.01661   0.01001  -0.0626   0.2065   1.0000
   9.500   1.3184   0.01708   0.01047  -0.0610   0.2001   1.0000
   9.750   1.3349   0.01755   0.01095  -0.0594   0.1941   1.0000
  10.000   1.3520   0.01800   0.01141  -0.0580   0.1873   1.0000
  10.250   1.3668   0.01858   0.01197  -0.0564   0.1787   1.0000
  10.500   1.3802   0.01926   0.01260  -0.0546   0.1663   1.0000
  10.750   1.3919   0.02006   0.01333  -0.0528   0.1492   1.0000
  11.000   1.3954   0.02138   0.01447  -0.0502   0.1216   1.0000
  11.250   1.3921   0.02323   0.01611  -0.0471   0.0914   1.0000
  11.500   1.3932   0.02489   0.01767  -0.0446   0.0755   1.0000
  11.750   1.3997   0.02624   0.01901  -0.0428   0.0691   1.0000
  12.000   1.4085   0.02746   0.02025  -0.0413   0.0660   1.0000
  12.250   1.4152   0.02890   0.02170  -0.0397   0.0624   1.0000
  12.500   1.4249   0.03012   0.02298  -0.0385   0.0600   1.0000
  12.750   1.4337   0.03145   0.02436  -0.0373   0.0581   1.0000
  13.000   1.4392   0.03309   0.02603  -0.0360   0.0556   1.0000
  13.250   1.4447   0.03479   0.02776  -0.0348   0.0531   1.0000
  13.500   1.4555   0.03606   0.02910  -0.0340   0.0512   1.0000
  13.750   1.4625   0.03770   0.03078  -0.0331   0.0488   1.0000
  14.000   1.4671   0.03961   0.03273  -0.0322   0.0468   1.0000
  14.250   1.4746   0.04129   0.03446  -0.0315   0.0446   1.0000
  14.500   1.4820   0.04301   0.03624  -0.0309   0.0419   1.0000
  14.750   1.4855   0.04517   0.03841  -0.0302   0.0379   1.0000
  15.000   1.4868   0.04762   0.04085  -0.0297   0.0276   1.0000
  15.250   1.4756   0.05148   0.04466  -0.0292   0.0193   1.0000
  15.500   1.4660   0.05535   0.04861  -0.0290   0.0173   1.0000
  15.750   1.4598   0.05898   0.05234  -0.0290   0.0166   1.0000
  16.000   1.4540   0.06267   0.05614  -0.0291   0.0161   1.0000
  16.250   1.4478   0.06650   0.06008  -0.0295   0.0157   1.0000
  16.500   1.4391   0.07079   0.06449  -0.0300   0.0153   1.0000
  16.750   1.4326   0.07489   0.06870  -0.0307   0.0151   1.0000
  17.000   1.4244   0.07933   0.07328  -0.0316   0.0149   1.0000
  17.250   1.4158   0.08393   0.07799  -0.0327   0.0147   1.0000
  17.500   1.4058   0.08885   0.08305  -0.0340   0.0145   1.0000
  17.750   1.3944   0.09410   0.08842  -0.0356   0.0144   1.0000
  18.000   1.3826   0.09949   0.09394  -0.0373   0.0143   1.0000
  18.250   1.3705   0.10502   0.09959  -0.0393   0.0142   1.0000
  18.500   1.3584   0.11065   0.10535  -0.0413   0.0141   1.0000
  18.750   1.3447   0.11664   0.11145  -0.0437   0.0139   1.0000
<< Back to GOE 619 AIRFOIL (goe619-il)

Polar data table (+)

Polar graphs


<< Back to GOE 619 AIRFOIL (goe619-il)