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GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 528 AIRFOIL (goe528-il)
Reynolds number: 200,000
Max Cl/Cd: 77.6 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe528-il-200000-n5.txt
Download as CSV file: xf-goe528-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 528 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.2420   0.14159   0.13780  -0.0421   1.0000   0.0270
 -12.750  -0.2398   0.13872   0.13496  -0.0430   1.0000   0.0270
 -12.500  -0.2377   0.13585   0.13212  -0.0438   1.0000   0.0271
 -12.250  -0.2314   0.13281   0.12912  -0.0434   1.0000   0.0274
 -12.000  -0.2246   0.13050   0.12684  -0.0429   1.0000   0.0280
 -11.750  -0.2209   0.12815   0.12453  -0.0428   1.0000   0.0284
 -11.500  -0.2184   0.12593   0.12237  -0.0425   1.0000   0.0294
 -11.250  -0.2039   0.12180   0.11824  -0.0463   0.9948   0.0305
 -10.750  -0.1862   0.11349   0.10992  -0.0553   0.9757   0.0318
 -10.500  -0.1776   0.10923   0.10567  -0.0598   0.9650   0.0319
 -10.000  -0.1369   0.10213   0.09854  -0.0643   0.9484   0.0335
  -9.750  -0.1173   0.09844   0.09482  -0.0688   0.9394   0.0348
  -9.500  -0.1042   0.09347   0.08982  -0.0778   0.9291   0.0374
  -9.250  -0.0864   0.08814   0.08443  -0.0859   0.9184   0.0376
  -9.000  -0.0672   0.08339   0.07963  -0.0921   0.9069   0.0376
  -8.500  -0.0181   0.07756   0.07369  -0.0970   0.8865   0.0400
  -8.250  -0.0225   0.07132   0.06739  -0.1044   0.8687   0.0381
  -8.000  -0.0036   0.06966   0.06566  -0.1038   0.8582   0.0359
  -7.750  -0.0023   0.06640   0.06236  -0.1053   0.8447   0.0347
  -7.500  -0.0070   0.06230   0.05821  -0.1081   0.8319   0.0335
  -7.250  -0.0029   0.05895   0.05482  -0.1107   0.8202   0.0338
  -7.000   0.0049   0.05572   0.05153  -0.1133   0.8100   0.0347
  -6.750   0.0122   0.05122   0.04691  -0.1172   0.8003   0.0350
  -6.500   0.0199   0.04575   0.04128  -0.1212   0.7905   0.0345
  -6.000   0.0416   0.03445   0.02930  -0.1264   0.7731   0.0352
  -5.750   0.0551   0.02947   0.02373  -0.1271   0.7656   0.0360
  -5.500   0.0718   0.02617   0.01993  -0.1267   0.7569   0.0363
  -5.250   0.0921   0.02370   0.01694  -0.1261   0.7493   0.0368
  -4.750   0.1375   0.02084   0.01337  -0.1249   0.7322   0.0385
  -4.500   0.1614   0.01991   0.01227  -0.1242   0.7229   0.0390
  -4.250   0.1865   0.01904   0.01117  -0.1237   0.7148   0.0395
  -4.000   0.2112   0.01828   0.01023  -0.1231   0.7050   0.0400
  -3.750   0.2366   0.01759   0.00935  -0.1225   0.6963   0.0406
  -3.500   0.2620   0.01698   0.00859  -0.1219   0.6865   0.0414
  -3.250   0.2877   0.01649   0.00794  -0.1213   0.6774   0.0426
  -3.000   0.3134   0.01604   0.00733  -0.1207   0.6677   0.0437
  -2.750   0.3390   0.01562   0.00678  -0.1201   0.6579   0.0443
  -2.250   0.3895   0.01478   0.00586  -0.1188   0.6387   0.0460
  -2.000   0.4149   0.01451   0.00553  -0.1182   0.6296   0.0472
  -1.750   0.4403   0.01428   0.00524  -0.1176   0.6201   0.0485
  -1.500   0.4658   0.01411   0.00500  -0.1171   0.6112   0.0505
  -1.250   0.4912   0.01394   0.00477  -0.1165   0.6024   0.0529
  -1.000   0.5167   0.01380   0.00460  -0.1159   0.5939   0.0556
  -0.750   0.5423   0.01371   0.00443  -0.1153   0.5858   0.0590
  -0.500   0.5680   0.01360   0.00430  -0.1148   0.5780   0.0645
  -0.250   0.5935   0.01351   0.00420  -0.1142   0.5705   0.0768
   0.000   0.6188   0.01337   0.00414  -0.1137   0.5636   0.1116
   0.250   0.6432   0.01311   0.00417  -0.1132   0.5564   0.2081
   0.500   0.6673   0.01292   0.00422  -0.1126   0.5502   0.3217
   0.750   0.6895   0.01253   0.00434  -0.1116   0.5436   0.4955
   1.000   0.7451   0.01170   0.00444  -0.1171   0.5362   1.0000
   1.250   0.7700   0.01186   0.00449  -0.1164   0.5301   1.0000
   1.500   0.7948   0.01202   0.00456  -0.1158   0.5238   1.0000
   1.750   0.8195   0.01221   0.00462  -0.1151   0.5182   1.0000
   2.000   0.8444   0.01237   0.00473  -0.1145   0.5123   1.0000
   2.250   0.8690   0.01254   0.00483  -0.1138   0.5062   1.0000
   2.500   0.8936   0.01275   0.00492  -0.1131   0.5008   1.0000
   2.750   0.9182   0.01291   0.00507  -0.1125   0.4947   1.0000
   3.000   0.9425   0.01310   0.00521  -0.1118   0.4886   1.0000
   3.250   0.9669   0.01332   0.00533  -0.1111   0.4832   1.0000
   3.500   0.9910   0.01349   0.00552  -0.1104   0.4767   1.0000
   3.750   1.0149   0.01370   0.00567  -0.1097   0.4705   1.0000
   4.000   1.0387   0.01391   0.00584  -0.1089   0.4647   1.0000
   4.250   1.0622   0.01410   0.00604  -0.1082   0.4579   1.0000
   4.500   1.0854   0.01433   0.00621  -0.1073   0.4518   1.0000
   4.750   1.1085   0.01453   0.00643  -0.1065   0.4450   1.0000
   5.000   1.1312   0.01475   0.00664  -0.1056   0.4383   1.0000
   5.250   1.1537   0.01499   0.00686  -0.1047   0.4322   1.0000
   5.500   1.1760   0.01522   0.00710  -0.1037   0.4252   1.0000
   5.750   1.1978   0.01548   0.00734  -0.1027   0.4191   1.0000
   6.000   1.2197   0.01572   0.00762  -0.1017   0.4124   1.0000
   6.250   1.2408   0.01599   0.00788  -0.1006   0.4059   1.0000
   6.500   1.2616   0.01627   0.00818  -0.0995   0.3993   1.0000
   6.750   1.2819   0.01655   0.00849  -0.0982   0.3922   1.0000
   7.000   1.3014   0.01687   0.00879  -0.0969   0.3861   1.0000
   7.250   1.3211   0.01716   0.00914  -0.0956   0.3791   1.0000
   7.500   1.3385   0.01751   0.00948  -0.0939   0.3721   1.0000
   7.750   1.3554   0.01784   0.00986  -0.0921   0.3646   1.0000
   8.000   1.3702   0.01822   0.01024  -0.0900   0.3572   1.0000
   8.250   1.3855   0.01861   0.01067  -0.0881   0.3493   1.0000
   8.500   1.3994   0.01906   0.01112  -0.0859   0.3417   1.0000
   8.750   1.4138   0.01952   0.01162  -0.0839   0.3338   1.0000
   9.000   1.4252   0.02007   0.01216  -0.0816   0.3250   1.0000
   9.250   1.4395   0.02059   0.01274  -0.0798   0.3174   1.0000
   9.500   1.4514   0.02121   0.01337  -0.0777   0.3103   1.0000
   9.750   1.4646   0.02182   0.01404  -0.0758   0.3031   1.0000
  10.000   1.4757   0.02253   0.01478  -0.0738   0.2960   1.0000
  10.250   1.4874   0.02326   0.01556  -0.0720   0.2892   1.0000
  10.500   1.4982   0.02406   0.01642  -0.0701   0.2823   1.0000
  10.750   1.5079   0.02495   0.01735  -0.0683   0.2757   1.0000
  11.000   1.5182   0.02585   0.01832  -0.0666   0.2689   1.0000
  11.250   1.5260   0.02693   0.01941  -0.0647   0.2630   1.0000
  11.500   1.5368   0.02789   0.02049  -0.0632   0.2567   1.0000
  11.750   1.5436   0.02911   0.02175  -0.0615   0.2501   1.0000
  12.000   1.5507   0.03036   0.02307  -0.0599   0.2427   1.0000
  12.250   1.5555   0.03182   0.02457  -0.0583   0.2356   1.0000
  12.500   1.5623   0.03320   0.02604  -0.0569   0.2297   1.0000
  12.750   1.5680   0.03472   0.02764  -0.0556   0.2234   1.0000
  13.000   1.5708   0.03649   0.02947  -0.0542   0.2169   1.0000
  13.250   1.5735   0.03836   0.03142  -0.0530   0.2088   1.0000
  13.500   1.5737   0.04050   0.03361  -0.0518   0.2005   1.0000
  13.750   1.5700   0.04308   0.03622  -0.0506   0.1907   1.0000
  14.000   1.5678   0.04569   0.03888  -0.0498   0.1798   1.0000
  14.250   1.5634   0.04861   0.04185  -0.0490   0.1690   1.0000
  14.500   1.5558   0.05201   0.04527  -0.0485   0.1562   1.0000
  14.750   1.5477   0.05562   0.04891  -0.0481   0.1426   1.0000
  15.000   1.5351   0.05992   0.05318  -0.0480   0.1253   1.0000
  15.250   1.5176   0.06498   0.05818  -0.0483   0.1076   1.0000
  15.500   1.5006   0.07018   0.06334  -0.0487   0.0967   1.0000
  15.750   1.4855   0.07527   0.06844  -0.0494   0.0900   1.0000
  16.000   1.4754   0.07985   0.07308  -0.0500   0.0856   1.0000
  16.250   1.4647   0.08460   0.07791  -0.0509   0.0819   1.0000
  16.500   1.4528   0.08963   0.08301  -0.0519   0.0787   1.0000
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