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WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)
Reynolds number: 200,000
Max Cl/Cd: 82.91 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601261-il-200000.txt
Download as CSV file: xf-fx601261-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 60-126/1 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3126   0.10603   0.10252  -0.0402   1.0000   0.0557
  -9.500  -0.3112   0.10306   0.09960  -0.0408   1.0000   0.0579
  -9.250  -0.3195   0.09936   0.09598  -0.0435   1.0000   0.0610
  -9.000  -0.3003   0.09179   0.08897  -0.0372   1.0000   0.0636
  -8.750  -0.2777   0.08876   0.08593  -0.0374   0.9979   0.0652
  -8.500  -0.2607   0.08468   0.08185  -0.0400   0.9950   0.0672
  -8.250  -0.2506   0.07981   0.07698  -0.0438   0.9913   0.0700
  -8.000  -0.2928   0.06742   0.06463  -0.0630   0.9824   0.0755
  -7.500  -0.3750   0.06732   0.06417  -0.0777   0.9770   0.0754
  -7.250  -0.3552   0.06330   0.06038  -0.0736   0.9752   0.0775
  -7.000  -0.3262   0.06306   0.06019  -0.0703   0.9728   0.0795
  -6.500  -0.2393   0.01915   0.01461  -0.1104   0.9415   0.0535
  -6.250  -0.2408   0.02789   0.02195  -0.1120   0.9468   0.0309
  -6.000  -0.2001   0.02400   0.01766  -0.1154   0.9448   0.0276
  -5.750  -0.1671   0.02234   0.01553  -0.1159   0.9374   0.0252
  -5.500  -0.1273   0.02065   0.01373  -0.1181   0.9343   0.0246
  -5.250  -0.0863   0.01892   0.01195  -0.1207   0.9319   0.0242
  -5.000  -0.0520   0.01773   0.01072  -0.1220   0.9263   0.0241
  -4.750  -0.0151   0.01665   0.00960  -0.1239   0.9208   0.0244
  -4.500   0.0264   0.01564   0.00849  -0.1268   0.9170   0.0250
  -4.250   0.0601   0.01483   0.00758  -0.1282   0.9097   0.0284
  -4.000   0.0978   0.01422   0.00685  -0.1300   0.9036   0.0326
  -3.750   0.1318   0.01369   0.00624  -0.1310   0.8957   0.0415
  -3.500   0.1671   0.01218   0.00555  -0.1335   0.8882   0.2302
  -3.250   0.1973   0.01183   0.00552  -0.1341   0.8796   0.3380
  -3.000   0.2294   0.01183   0.00558  -0.1345   0.8720   0.3979
  -2.750   0.2567   0.01207   0.00584  -0.1340   0.8625   0.4408
  -2.500   0.2877   0.01225   0.00598  -0.1341   0.8554   0.4680
  -2.250   0.3136   0.01248   0.00615  -0.1333   0.8450   0.4909
  -2.000   0.3418   0.01255   0.00617  -0.1329   0.8359   0.5058
  -1.750   0.3700   0.01252   0.00611  -0.1326   0.8268   0.5158
  -1.500   0.3969   0.01253   0.00607  -0.1321   0.8166   0.5263
  -1.250   0.4265   0.01254   0.00595  -0.1321   0.8086   0.5375
  -1.000   0.4529   0.01252   0.00596  -0.1315   0.7985   0.5461
  -0.750   0.4806   0.01252   0.00591  -0.1312   0.7894   0.5563
  -0.500   0.5094   0.01251   0.00582  -0.1310   0.7804   0.5674
  -0.250   0.5355   0.01248   0.00581  -0.1304   0.7694   0.5759
   0.000   0.5632   0.01245   0.00573  -0.1301   0.7592   0.5856
   0.250   0.5915   0.01241   0.00564  -0.1299   0.7499   0.5952
   0.500   0.6181   0.01239   0.00564  -0.1294   0.7388   0.6039
   0.750   0.6459   0.01239   0.00561  -0.1292   0.7289   0.6144
   1.000   0.6738   0.01237   0.00556  -0.1289   0.7195   0.6250
   1.250   0.7001   0.01236   0.00558  -0.1283   0.7076   0.6360
   1.500   0.7271   0.01235   0.00558  -0.1279   0.6959   0.6473
   1.750   0.7544   0.01235   0.00557  -0.1276   0.6845   0.6591
   2.000   0.7814   0.01235   0.00555  -0.1272   0.6731   0.6708
   2.250   0.8078   0.01235   0.00558  -0.1266   0.6606   0.6837
   2.500   0.8337   0.01236   0.00564  -0.1260   0.6472   0.6976
   2.750   0.8593   0.01237   0.00566  -0.1253   0.6327   0.7129
   3.000   0.8846   0.01238   0.00569  -0.1245   0.6175   0.7306
   3.250   0.9095   0.01240   0.00574  -0.1237   0.6024   0.7514
   3.500   0.9336   0.01242   0.00584  -0.1227   0.5876   0.7763
   3.750   0.9563   0.01241   0.00591  -0.1214   0.5726   0.8102
   4.000   0.9734   0.01227   0.00592  -0.1187   0.5582   0.8764
   4.250   0.9994   0.01229   0.00595  -0.1183   0.5427   1.0000
   4.500   1.0269   0.01253   0.00612  -0.1183   0.5280   1.0000
   4.750   1.0533   0.01278   0.00630  -0.1181   0.5129   1.0000
   5.000   1.0788   0.01304   0.00650  -0.1176   0.4966   1.0000
   5.250   1.1034   0.01332   0.00671  -0.1170   0.4787   1.0000
   5.500   1.1276   0.01360   0.00695  -0.1163   0.4594   1.0000
   5.750   1.1513   0.01391   0.00722  -0.1156   0.4397   1.0000
   6.000   1.1746   0.01426   0.00751  -0.1148   0.4213   1.0000
   6.250   1.1977   0.01464   0.00784  -0.1139   0.4033   1.0000
   6.500   1.2205   0.01501   0.00820  -0.1131   0.3840   1.0000
   6.750   1.2423   0.01545   0.00860  -0.1121   0.3636   1.0000
   7.000   1.2631   0.01594   0.00902  -0.1109   0.3428   1.0000
   7.250   1.2836   0.01644   0.00949  -0.1098   0.3204   1.0000
   7.500   1.3026   0.01704   0.01001  -0.1084   0.2978   1.0000
   7.750   1.3206   0.01769   0.01060  -0.1069   0.2745   1.0000
   8.000   1.3377   0.01840   0.01124  -0.1053   0.2505   1.0000
   8.250   1.3525   0.01923   0.01196  -0.1034   0.2287   1.0000
   8.500   1.3674   0.02006   0.01273  -0.1016   0.2083   1.0000
   8.750   1.3806   0.02094   0.01355  -0.0995   0.1901   1.0000
   9.000   1.3913   0.02186   0.01442  -0.0970   0.1756   1.0000
   9.250   1.4018   0.02279   0.01533  -0.0945   0.1630   1.0000
   9.500   1.4117   0.02377   0.01629  -0.0921   0.1517   1.0000
   9.750   1.4198   0.02485   0.01731  -0.0896   0.1414   1.0000
  10.000   1.4298   0.02586   0.01835  -0.0875   0.1315   1.0000
  10.250   1.4390   0.02698   0.01951  -0.0854   0.1230   1.0000
  10.500   1.4452   0.02831   0.02081  -0.0832   0.1151   1.0000
  10.750   1.4568   0.02933   0.02195  -0.0817   0.1071   1.0000
  11.000   1.4621   0.03084   0.02344  -0.0797   0.1008   1.0000
  11.250   1.4718   0.03212   0.02484  -0.0783   0.0950   1.0000
  11.500   1.4760   0.03386   0.02658  -0.0766   0.0902   1.0000
  11.750   1.4829   0.03550   0.02832  -0.0751   0.0855   1.0000
  12.000   1.4908   0.03707   0.03000  -0.0739   0.0802   1.0000
  12.250   1.4924   0.03926   0.03219  -0.0726   0.0760   1.0000
  12.500   1.5020   0.04078   0.03387  -0.0718   0.0714   1.0000
  12.750   1.5080   0.04267   0.03583  -0.0710   0.0668   1.0000
  13.000   1.5106   0.04498   0.03817  -0.0703   0.0629   1.0000
  13.250   1.5162   0.04707   0.04040  -0.0696   0.0600   1.0000
  13.500   1.5192   0.04949   0.04291  -0.0691   0.0574   1.0000
  13.750   1.5193   0.05231   0.04579  -0.0688   0.0551   1.0000
  14.000   1.5161   0.05560   0.04912  -0.0685   0.0529   1.0000
  14.250   1.5227   0.05786   0.05158  -0.0684   0.0512   1.0000
  14.500   1.5267   0.06050   0.05439  -0.0684   0.0492   1.0000
  14.750   1.5300   0.06330   0.05734  -0.0687   0.0467   1.0000
  15.000   1.5304   0.06657   0.06071  -0.0692   0.0442   1.0000
  15.250   1.5279   0.07035   0.06457  -0.0699   0.0426   1.0000
  15.500   1.5310   0.07343   0.06786  -0.0705   0.0407   1.0000
  15.750   1.5318   0.07694   0.07152  -0.0713   0.0387   1.0000
  16.000   1.5293   0.08105   0.07572  -0.0726   0.0362   1.0000
  16.250   1.5222   0.08600   0.08072  -0.0744   0.0337   1.0000
  16.500   1.5191   0.09039   0.08529  -0.0759   0.0316   1.0000
  16.750   1.5118   0.09562   0.09063  -0.0779   0.0295   1.0000
  17.000   1.5007   0.10164   0.09676  -0.0805   0.0278   1.0000
  17.250   1.4875   0.10819   0.10342  -0.0834   0.0264   1.0000
  17.500   1.4868   0.11253   0.10800  -0.0853   0.0228   1.0000
  17.750   1.4762   0.11887   0.11448  -0.0884   0.0198   1.0000
  18.000   1.4673   0.12494   0.12071  -0.0915   0.0167   1.0000
  18.250   1.4529   0.13225   0.12813  -0.0956   0.0146   1.0000
  18.500   1.4383   0.13978   0.13579  -0.0999   0.0136   1.0000
  18.750   1.4231   0.14763   0.14377  -0.1047   0.0129   1.0000
  19.000   1.4085   0.15552   0.15181  -0.1096   0.0126   1.0000
  19.250   1.3943   0.16349   0.15993  -0.1147   0.0126   1.0000
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