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GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 527 AIRFOIL (goe527-il)
Reynolds number: 50,000
Max Cl/Cd: 15.89 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe527-il-50000-n5.txt
Download as CSV file: xf-goe527-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 527 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1810   0.11339   0.10663  -0.0676   0.9566   0.0956
 -10.000  -0.1591   0.10954   0.10273  -0.0696   0.9477   0.0944
  -9.750  -0.1425   0.10510   0.09826  -0.0741   0.9407   0.0939
  -9.500  -0.1309   0.10112   0.09426  -0.0773   0.9305   0.0933
  -9.250  -0.1146   0.09655   0.08966  -0.0820   0.9240   0.0921
  -9.000  -0.1069   0.09245   0.08555  -0.0854   0.9133   0.0907
  -8.750  -0.0958   0.08738   0.08045  -0.0910   0.9061   0.0894
  -8.500  -0.0956   0.08332   0.07638  -0.0941   0.8935   0.0892
  -8.250  -0.0947   0.07875   0.07178  -0.0983   0.8829   0.0893
  -8.000  -0.1025   0.07403   0.06702  -0.1022   0.8704   0.0892
  -7.750  -0.1163   0.06943   0.06235  -0.1046   0.8565   0.0891
  -7.500  -0.1236   0.06460   0.05734  -0.1072   0.8462   0.0892
  -7.250  -0.1332   0.06061   0.05316  -0.1076   0.8342   0.0892
  -7.000  -0.1394   0.05705   0.04933  -0.1073   0.8231   0.0893
  -6.750  -0.1357   0.05337   0.04530  -0.1077   0.8144   0.0899
  -6.500  -0.1340   0.05071   0.04232  -0.1064   0.8041   0.0910
  -6.250  -0.1238   0.04772   0.03885  -0.1061   0.7962   0.0932
  -6.000  -0.1164   0.04514   0.03567  -0.1047   0.7874   0.0953
  -5.750  -0.0980   0.04370   0.03415  -0.1039   0.7794   0.0973
  -5.500  -0.0699   0.04185   0.03206  -0.1045   0.7746   0.0998
  -5.250  -0.0618   0.04094   0.03093  -0.1020   0.7639   0.1021
  -5.000  -0.0370   0.03917   0.02862  -0.1019   0.7582   0.1067
  -4.750  -0.0177   0.03815   0.02749  -0.1008   0.7507   0.1102
  -4.500   0.0017   0.03738   0.02660  -0.0997   0.7429   0.1142
  -4.250   0.0323   0.03610   0.02488  -0.1000   0.7383   0.1209
  -4.000   0.0464   0.03570   0.02451  -0.0981   0.7296   0.1251
  -3.750   0.0704   0.03506   0.02374  -0.0975   0.7232   0.1325
  -3.500   0.1033   0.03410   0.02266  -0.0980   0.7191   0.1410
  -3.250   0.1145   0.03415   0.02265  -0.0956   0.7100   0.1478
  -3.000   0.1401   0.03367   0.02211  -0.0952   0.7042   0.1570
  -2.750   0.1743   0.03300   0.02128  -0.0959   0.7004   0.1694
  -2.500   0.1845   0.03327   0.02161  -0.0935   0.6916   0.1773
  -2.250   0.2107   0.03300   0.02128  -0.0931   0.6858   0.1898
  -2.000   0.2445   0.03246   0.02066  -0.0937   0.6820   0.2061
  -1.750   0.2541   0.03288   0.02111  -0.0913   0.6740   0.2193
  -1.500   0.2752   0.03282   0.02110  -0.0903   0.6679   0.2396
  -1.250   0.3062   0.03225   0.02070  -0.0906   0.6641   0.2777
  -1.000   0.3181   0.03245   0.02118  -0.0885   0.6571   0.3266
  -0.750   0.3300   0.03254   0.02169  -0.0863   0.6503   0.4118
  -0.500   0.3536   0.03193   0.02164  -0.0848   0.6464   0.5627
  -0.250   0.4495   0.03072   0.02121  -0.0946   0.6444   0.9650
   0.000   0.4533   0.03211   0.02246  -0.0923   0.6350   1.0000
   0.250   0.4730   0.03251   0.02262  -0.0911   0.6299   1.0000
   0.500   0.5045   0.03251   0.02234  -0.0913   0.6265   1.0000
   0.750   0.4904   0.03422   0.02399  -0.0860   0.6167   1.0000
   1.000   0.5117   0.03464   0.02421  -0.0850   0.6116   1.0000
   1.250   0.5448   0.03462   0.02397  -0.0854   0.6085   1.0000
   1.500   0.5233   0.03675   0.02608  -0.0795   0.5979   1.0000
   1.750   0.5473   0.03709   0.02625  -0.0789   0.5932   1.0000
   2.000   0.5834   0.03697   0.02595  -0.0796   0.5903   1.0000
   2.500   0.5846   0.03975   0.02857  -0.0734   0.5744   1.0000
   2.750   0.6223   0.03946   0.02812  -0.0741   0.5718   1.0000
   3.250   0.6272   0.04238   0.03093  -0.0689   0.5554   1.0000
   3.500   0.6656   0.04189   0.03029  -0.0694   0.5529   1.0000
   4.000   0.6761   0.04467   0.03299  -0.0651   0.5362   1.0000
   4.500   0.6896   0.04753   0.03576  -0.0616   0.5193   1.0000
   4.750   0.7292   0.04661   0.03474  -0.0617   0.5170   1.0000
   5.250   0.7282   0.05071   0.03881  -0.0578   0.4972   1.0000
   5.750   0.7548   0.05282   0.04087  -0.0556   0.4825   1.0000
   6.250   0.7679   0.05628   0.04431  -0.0531   0.4654   1.0000
   6.500   0.7531   0.06011   0.04818  -0.0516   0.4521   1.0000
   6.750   0.7807   0.05993   0.04796  -0.0510   0.4484   1.0000
   7.000   0.8138   0.05914   0.04712  -0.0503   0.4461   1.0000
   7.250   0.7939   0.06367   0.05171  -0.0491   0.4317   1.0000
   7.500   0.8253   0.06301   0.05102  -0.0484   0.4293   1.0000
   7.750   0.8044   0.06792   0.05598  -0.0475   0.4153   1.0000
   8.000   0.8337   0.06749   0.05554  -0.0468   0.4127   1.0000
   8.500   0.8416   0.07218   0.06026  -0.0455   0.3964   1.0000
   9.000   0.8460   0.07758   0.06571  -0.0446   0.3807   1.0000
   9.500   0.8450   0.08402   0.07223  -0.0441   0.3656   1.0000
   9.750   0.8713   0.08388   0.07209  -0.0434   0.3632   1.0000
  10.000   0.8437   0.09068   0.07896  -0.0440   0.3511   1.0000
  10.250   0.8654   0.09122   0.07952  -0.0435   0.3483   1.0000
  10.750   0.8554   0.09945   0.08786  -0.0442   0.3343   1.0000
  11.000   0.8795   0.09958   0.08801  -0.0436   0.3317   1.0000
  11.250   0.8526   0.10679   0.09530  -0.0449   0.3217   1.0000
  11.500   0.8700   0.10779   0.09634  -0.0445   0.3177   1.0000
  11.750   0.8981   0.10718   0.09576  -0.0437   0.3152   1.0000
  12.000   0.8723   0.11410   0.10275  -0.0452   0.3039   1.0000
  12.250   0.8963   0.11398   0.10267  -0.0445   0.3005   1.0000
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