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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 500,000
Max Cl/Cd: 116.71 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe195-il-500000.txt
Download as CSV file: xf-goe195-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 195 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3318   0.09503   0.09274  -0.0316   1.0000   0.0267
  -8.250  -0.3502   0.09271   0.09048  -0.0310   1.0000   0.0273
  -8.000  -0.3668   0.09115   0.08898  -0.0282   1.0000   0.0274
  -7.750  -0.3532   0.08597   0.08380  -0.0351   0.9966   0.0276
  -7.500  -0.3371   0.07983   0.07766  -0.0407   0.9942   0.0281
  -7.250  -0.3167   0.07716   0.07499  -0.0433   0.9914   0.0285
  -7.000  -0.2926   0.07433   0.07214  -0.0472   0.9883   0.0293
  -6.750  -0.2640   0.07029   0.06808  -0.0543   0.9854   0.0306
  -6.500  -0.2136   0.05903   0.05672  -0.0780   0.9790   0.0339
  -6.250  -0.1848   0.05089   0.04853  -0.0891   0.9749   0.0350
  -6.000  -0.1520   0.04853   0.04614  -0.0936   0.9731   0.0358
  -5.750  -0.0831   0.03015   0.02682  -0.1239   0.9693   0.0430
  -5.500  -0.0564   0.02835   0.02509  -0.1250   0.9642   0.0441
  -5.250  -0.0235   0.02662   0.02330  -0.1275   0.9607   0.0458
  -5.000   0.0162   0.02358   0.01957  -0.1323   0.9575   0.0528
  -4.750   0.0417   0.02163   0.01769  -0.1329   0.9504   0.0548
  -4.500   0.0720   0.02054   0.01654  -0.1338   0.9445   0.0580
  -4.000   0.1364   0.01487   0.00959  -0.1351   0.9303   0.0428
  -3.750   0.1649   0.01363   0.00826  -0.1350   0.9225   0.0407
  -3.500   0.1932   0.01254   0.00701  -0.1349   0.9138   0.0400
  -3.250   0.2210   0.01186   0.00622  -0.1346   0.9034   0.0404
  -3.000   0.2491   0.01115   0.00541  -0.1344   0.8929   0.0402
  -2.750   0.2770   0.01056   0.00473  -0.1341   0.8814   0.0402
  -2.500   0.3047   0.01010   0.00419  -0.1338   0.8682   0.0405
  -2.250   0.3324   0.00971   0.00373  -0.1335   0.8543   0.0408
  -2.000   0.3602   0.00940   0.00334  -0.1332   0.8393   0.0411
  -1.750   0.3879   0.00915   0.00300  -0.1329   0.8233   0.0415
  -1.500   0.4156   0.00896   0.00273  -0.1326   0.8073   0.0421
  -1.250   0.4435   0.00869   0.00235  -0.1324   0.7912   0.0438
  -1.000   0.4711   0.00856   0.00212  -0.1321   0.7751   0.0452
  -0.750   0.4987   0.00849   0.00195  -0.1318   0.7591   0.0472
  -0.500   0.5262   0.00847   0.00183  -0.1314   0.7433   0.0499
  -0.250   0.5537   0.00845   0.00175  -0.1311   0.7271   0.0573
   0.000   0.5812   0.00804   0.00178  -0.1312   0.7102   0.2208
   0.250   0.6083   0.00810   0.00187  -0.1309   0.6903   0.2681
   0.500   0.6349   0.00820   0.00191  -0.1304   0.6660   0.2906
   0.750   0.6615   0.00829   0.00193  -0.1300   0.6374   0.3067
   1.000   0.6881   0.00839   0.00195  -0.1296   0.6116   0.3200
   1.250   0.7148   0.00850   0.00199  -0.1293   0.5930   0.3340
   1.500   0.7417   0.00858   0.00207  -0.1290   0.5784   0.3554
   1.750   0.7686   0.00864   0.00217  -0.1288   0.5651   0.3838
   2.000   0.7954   0.00861   0.00234  -0.1286   0.5536   0.4789
   2.250   0.8214   0.00842   0.00255  -0.1283   0.5434   0.6546
   2.500   0.8449   0.00791   0.00260  -0.1271   0.5342   1.0000
   2.750   0.8719   0.00812   0.00272  -0.1268   0.5260   1.0000
   3.000   0.8994   0.00825   0.00283  -0.1266   0.5182   1.0000
   3.250   0.9263   0.00846   0.00298  -0.1263   0.5095   1.0000
   3.500   0.9533   0.00861   0.00310  -0.1261   0.4984   1.0000
   3.750   0.9803   0.00875   0.00322  -0.1258   0.4876   1.0000
   4.000   1.0070   0.00893   0.00337  -0.1255   0.4775   1.0000
   4.250   1.0339   0.00906   0.00349  -0.1252   0.4662   1.0000
   4.500   1.0608   0.00920   0.00362  -0.1249   0.4533   1.0000
   4.750   1.0873   0.00935   0.00377  -0.1246   0.4381   1.0000
   5.000   1.1134   0.00954   0.00391  -0.1242   0.4193   1.0000
   5.250   1.1388   0.00980   0.00408  -0.1237   0.3902   1.0000
   5.500   1.1626   0.01021   0.00432  -0.1230   0.3519   1.0000
   5.750   1.1850   0.01080   0.00469  -0.1221   0.3073   1.0000
   6.000   1.2071   0.01144   0.00511  -0.1212   0.2672   1.0000
   6.250   1.2294   0.01207   0.00555  -0.1203   0.2303   1.0000
   6.500   1.2510   0.01275   0.00602  -0.1194   0.1936   1.0000
   6.750   1.2709   0.01362   0.00660  -0.1182   0.1411   1.0000
   7.000   1.2907   0.01446   0.00723  -0.1170   0.1078   1.0000
   7.250   1.3109   0.01524   0.00785  -0.1158   0.0794   1.0000
   7.500   1.3283   0.01628   0.00861  -0.1142   0.0454   1.0000
   7.750   1.3489   0.01696   0.00931  -0.1130   0.0394   1.0000
   8.000   1.3684   0.01771   0.01008  -0.1116   0.0359   1.0000
   8.250   1.3868   0.01854   0.01097  -0.1100   0.0332   1.0000
   8.500   1.4063   0.01920   0.01170  -0.1087   0.0316   1.0000
   8.750   1.4240   0.01997   0.01255  -0.1071   0.0299   1.0000
   9.000   1.4384   0.02098   0.01360  -0.1050   0.0282   1.0000
   9.250   1.4469   0.02238   0.01509  -0.1021   0.0266   1.0000
   9.500   1.4632   0.02307   0.01586  -0.1003   0.0257   1.0000
   9.750   1.4750   0.02391   0.01678  -0.0977   0.0247   1.0000
  10.000   1.4853   0.02486   0.01780  -0.0951   0.0238   1.0000
  10.250   1.4944   0.02591   0.01890  -0.0925   0.0229   1.0000
  10.500   1.4998   0.02726   0.02031  -0.0895   0.0220   1.0000
  10.750   1.4942   0.02964   0.02277  -0.0854   0.0211   1.0000
  11.000   1.5077   0.03046   0.02369  -0.0838   0.0206   1.0000
  11.250   1.5171   0.03167   0.02500  -0.0818   0.0200   1.0000
  11.500   1.5246   0.03310   0.02653  -0.0798   0.0194   1.0000
  11.750   1.5315   0.03464   0.02815  -0.0779   0.0188   1.0000
  12.000   1.5377   0.03628   0.02987  -0.0761   0.0182   1.0000
  12.250   1.5431   0.03804   0.03170  -0.0744   0.0178   1.0000
  12.500   1.5465   0.04008   0.03380  -0.0727   0.0174   1.0000
  12.750   1.5458   0.04271   0.03649  -0.0707   0.0169   1.0000
  13.000   1.5470   0.04523   0.03913  -0.0690   0.0165   1.0000
  13.250   1.5515   0.04731   0.04136  -0.0680   0.0161   1.0000
  13.500   1.5547   0.04961   0.04380  -0.0671   0.0157   1.0000
  13.750   1.5567   0.05212   0.04644  -0.0662   0.0153   1.0000
  14.000   1.5578   0.05475   0.04919  -0.0655   0.0150   1.0000
  14.250   1.5578   0.05759   0.05215  -0.0649   0.0147   1.0000
  14.500   1.5569   0.06061   0.05529  -0.0645   0.0144   1.0000
  14.750   1.5553   0.06375   0.05854  -0.0643   0.0142   1.0000
  15.000   1.5532   0.06706   0.06195  -0.0643   0.0139   1.0000
  15.250   1.5505   0.07053   0.06553  -0.0644   0.0137   1.0000
  15.500   1.5471   0.07419   0.06929  -0.0647   0.0135   1.0000
  15.750   1.5419   0.07811   0.07331  -0.0649   0.0133   1.0000
  16.000   1.5328   0.08262   0.07795  -0.0648   0.0131   1.0000
  16.250   1.5195   0.08801   0.08353  -0.0654   0.0130   1.0000
  16.500   1.5093   0.09326   0.08897  -0.0673   0.0129   1.0000
  16.750   1.4978   0.09883   0.09472  -0.0693   0.0128   1.0000
  17.000   1.4853   0.10479   0.10086  -0.0717   0.0127   1.0000
  17.250   1.4718   0.11111   0.10737  -0.0745   0.0127   1.0000
  17.500   1.4574   0.11779   0.11423  -0.0778   0.0126   1.0000
  17.750   1.4416   0.12499   0.12162  -0.0815   0.0126   1.0000
  18.000   1.4253   0.13260   0.12940  -0.0858   0.0126   1.0000
  18.250   1.4081   0.14082   0.13781  -0.0908   0.0125   1.0000
  18.500   1.3897   0.14973   0.14690  -0.0965   0.0125   1.0000
  18.750   1.3701   0.15937   0.15672  -0.1029   0.0126   1.0000
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