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EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1200 AIRFOIL (e1200-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.83 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1200-il-1000000.txt
Download as CSV file: xf-e1200-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1200 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.3407   0.16658   0.16478  -0.0470   1.0000   0.0151
 -16.250  -0.3360   0.16348   0.16170  -0.0481   1.0000   0.0156
 -16.000  -0.5820   0.09532   0.09323  -0.0754   1.0000   0.0146
 -15.750  -0.5587   0.09682   0.09482  -0.0739   1.0000   0.0148
 -15.500  -0.5354   0.09843   0.09651  -0.0724   1.0000   0.0150
 -15.250  -0.5049   0.09881   0.09694  -0.0739   0.9992   0.0153
 -15.000  -0.7354   0.05043   0.04729  -0.1075   0.9925   0.0142
 -14.750  -0.7367   0.04612   0.04282  -0.1114   0.9796   0.0142
 -14.500  -0.7248   0.04184   0.03838  -0.1175   0.9586   0.0144
 -14.250  -0.6958   0.03785   0.03419  -0.1264   0.9467   0.0145
 -14.000  -0.6576   0.03437   0.03050  -0.1359   0.9308   0.0147
 -13.750  -0.6330   0.03205   0.02789  -0.1408   0.8958   0.0148
 -13.500  -0.6299   0.03063   0.02624  -0.1399   0.8693   0.0149
 -13.250  -0.6265   0.02938   0.02485  -0.1386   0.8528   0.0151
 -13.000  -0.6221   0.02816   0.02348  -0.1373   0.8407   0.0152
 -12.750  -0.6167   0.02687   0.02206  -0.1360   0.8311   0.0152
 -12.500  -0.6093   0.02578   0.02085  -0.1347   0.8232   0.0153
 -12.250  -0.6006   0.02480   0.01978  -0.1334   0.8163   0.0156
 -12.000  -0.5913   0.02382   0.01868  -0.1320   0.8098   0.0156
 -11.750  -0.5809   0.02283   0.01761  -0.1306   0.8045   0.0158
 -11.500  -0.5693   0.02198   0.01667  -0.1293   0.7992   0.0159
 -11.250  -0.5575   0.02117   0.01576  -0.1278   0.7944   0.0162
 -11.000  -0.5445   0.02038   0.01489  -0.1264   0.7903   0.0163
 -10.750  -0.5311   0.01978   0.01423  -0.1250   0.7865   0.0165
 -10.500  -0.5179   0.01918   0.01355  -0.1234   0.7827   0.0167
 -10.250  -0.5057   0.01872   0.01300  -0.1215   0.7789   0.0170
 -10.000  -0.4923   0.01826   0.01246  -0.1196   0.7752   0.0171
  -9.750  -0.4746   0.01779   0.01195  -0.1184   0.7724   0.0172
  -9.500  -0.4620   0.01649   0.01058  -0.1167   0.7694   0.0176
  -9.250  -0.4457   0.01579   0.00986  -0.1154   0.7665   0.0180
  -9.000  -0.4272   0.01525   0.00928  -0.1143   0.7637   0.0182
  -8.750  -0.4070   0.01482   0.00880  -0.1134   0.7609   0.0185
  -8.500  -0.3858   0.01441   0.00836  -0.1127   0.7583   0.0189
  -8.250  -0.3642   0.01398   0.00791  -0.1120   0.7562   0.0192
  -8.000  -0.3415   0.01361   0.00751  -0.1114   0.7538   0.0197
  -7.750  -0.3187   0.01322   0.00709  -0.1109   0.7515   0.0201
  -7.500  -0.2950   0.01289   0.00672  -0.1104   0.7493   0.0205
  -7.250  -0.2705   0.01260   0.00639  -0.1101   0.7471   0.0208
  -7.000  -0.2478   0.01214   0.00587  -0.1095   0.7448   0.0214
  -6.750  -0.2239   0.01176   0.00545  -0.1092   0.7423   0.0222
  -6.500  -0.1987   0.01145   0.00514  -0.1090   0.7406   0.0230
  -6.250  -0.1728   0.01119   0.00487  -0.1088   0.7387   0.0239
  -6.000  -0.1464   0.01095   0.00463  -0.1088   0.7367   0.0248
  -5.750  -0.1199   0.01070   0.00435  -0.1087   0.7348   0.0258
  -5.500  -0.0937   0.01042   0.00406  -0.1086   0.7329   0.0276
  -5.250  -0.0666   0.01022   0.00384  -0.1087   0.7310   0.0295
  -5.000  -0.0396   0.01000   0.00362  -0.1087   0.7288   0.0335
  -4.750  -0.0131   0.00970   0.00341  -0.1088   0.7264   0.0525
  -4.500   0.0129   0.00929   0.00320  -0.1088   0.7249   0.0908
  -4.250   0.0399   0.00899   0.00304  -0.1090   0.7234   0.1231
  -4.000   0.0671   0.00870   0.00289  -0.1092   0.7215   0.1584
  -3.750   0.0946   0.00840   0.00274  -0.1094   0.7195   0.1996
  -3.500   0.1221   0.00806   0.00259  -0.1097   0.7176   0.2544
  -3.250   0.1491   0.00756   0.00241  -0.1101   0.7157   0.3446
  -3.000   0.1762   0.00700   0.00222  -0.1106   0.7139   0.4573
  -2.750   0.2047   0.00671   0.00218  -0.1110   0.7117   0.5428
  -2.500   0.2342   0.00669   0.00221  -0.1115   0.7095   0.5776
  -2.250   0.2634   0.00666   0.00222  -0.1118   0.7080   0.5986
  -2.000   0.2927   0.00665   0.00224  -0.1121   0.7060   0.6149
  -1.750   0.3220   0.00667   0.00227  -0.1124   0.7036   0.6293
  -1.500   0.3513   0.00668   0.00228  -0.1126   0.7009   0.6388
  -1.250   0.3806   0.00670   0.00226  -0.1129   0.6978   0.6453
  -1.000   0.4103   0.00678   0.00227  -0.1133   0.6939   0.6506
  -0.750   0.4387   0.00674   0.00227  -0.1134   0.6906   0.6561
  -0.500   0.4675   0.00674   0.00226  -0.1135   0.6863   0.6619
  -0.250   0.4963   0.00676   0.00224  -0.1137   0.6820   0.6677
   0.000   0.5251   0.00681   0.00228  -0.1139   0.6778   0.6740
   0.250   0.5538   0.00683   0.00233  -0.1140   0.6746   0.6797
   0.500   0.5828   0.00687   0.00235  -0.1143   0.6710   0.6840
   0.750   0.6113   0.00684   0.00235  -0.1145   0.6674   0.6881
   1.000   0.6399   0.00687   0.00236  -0.1146   0.6637   0.6910
   1.250   0.6686   0.00690   0.00238  -0.1149   0.6600   0.6935
   1.500   0.6973   0.00690   0.00240  -0.1151   0.6557   0.6961
   1.750   0.7258   0.00692   0.00241  -0.1153   0.6513   0.6985
   2.000   0.7540   0.00698   0.00242  -0.1154   0.6465   0.7004
   2.250   0.7823   0.00696   0.00244  -0.1156   0.6415   0.7030
   2.500   0.8103   0.00696   0.00246  -0.1157   0.6356   0.7055
   2.750   0.8376   0.00701   0.00249  -0.1156   0.6295   0.7077
   3.000   0.8654   0.00704   0.00254  -0.1157   0.6218   0.7100
   3.250   0.8921   0.00710   0.00258  -0.1156   0.6137   0.7124
   3.500   0.9192   0.00716   0.00263  -0.1155   0.6035   0.7149
   3.750   0.9452   0.00726   0.00270  -0.1152   0.5909   0.7170
   4.000   0.9699   0.00737   0.00277  -0.1147   0.5756   0.7195
   4.250   0.9927   0.00753   0.00287  -0.1138   0.5552   0.7219
   4.500   1.0135   0.00779   0.00304  -0.1126   0.5292   0.7243
   4.750   1.0315   0.00814   0.00326  -0.1108   0.4979   0.7270
   5.000   1.0475   0.00857   0.00353  -0.1087   0.4649   0.7298
   5.250   1.0621   0.00902   0.00383  -0.1064   0.4331   0.7324
   5.500   1.0763   0.00945   0.00412  -0.1040   0.4062   0.7346
   5.750   1.0884   0.00979   0.00438  -0.1011   0.3829   0.7378
   6.250   1.1115   0.01064   0.00506  -0.0954   0.3399   0.7438
   6.500   1.1251   0.01106   0.00541  -0.0930   0.3222   0.7470
   6.750   1.1384   0.01150   0.00578  -0.0907   0.3058   0.7500
   7.000   1.1515   0.01195   0.00618  -0.0883   0.2902   0.7531
   7.250   1.1647   0.01241   0.00660  -0.0861   0.2771   0.7565
   7.500   1.1786   0.01287   0.00704  -0.0841   0.2655   0.7600
   7.750   1.1933   0.01333   0.00749  -0.0822   0.2550   0.7638
   8.000   1.2068   0.01388   0.00799  -0.0802   0.2448   0.7674
   8.250   1.2207   0.01440   0.00851  -0.0784   0.2352   0.7715
   8.500   1.2355   0.01492   0.00903  -0.0767   0.2271   0.7757
   8.750   1.2487   0.01554   0.00963  -0.0749   0.2186   0.7801
   9.000   1.2643   0.01608   0.01018  -0.0735   0.2117   0.7844
   9.250   1.2781   0.01670   0.01081  -0.0719   0.2047   0.7895
   9.500   1.2925   0.01732   0.01146  -0.0705   0.1982   0.7952
   9.750   1.3074   0.01796   0.01210  -0.0691   0.1917   0.8009
  10.000   1.3200   0.01870   0.01285  -0.0675   0.1850   0.8073
  10.250   1.3359   0.01930   0.01349  -0.0664   0.1799   0.8145
  10.500   1.3484   0.02009   0.01429  -0.0648   0.1733   0.8224
  10.750   1.3625   0.02080   0.01503  -0.0636   0.1667   0.8319
  11.000   1.3763   0.02152   0.01581  -0.0622   0.1621   0.8435
  11.250   1.3874   0.02238   0.01670  -0.0607   0.1553   0.8593
  11.500   1.4001   0.02308   0.01749  -0.0592   0.1497   0.8842
  11.750   1.4113   0.02383   0.01839  -0.0577   0.1436   1.0000
  12.000   1.4260   0.02467   0.01924  -0.0568   0.1385   1.0000
  12.250   1.4382   0.02569   0.02023  -0.0558   0.1320   1.0000
  12.500   1.4505   0.02671   0.02124  -0.0547   0.1257   1.0000
  12.750   1.4633   0.02771   0.02224  -0.0538   0.1204   1.0000
  13.000   1.4736   0.02891   0.02342  -0.0526   0.1148   1.0000
  13.250   1.4874   0.02989   0.02441  -0.0518   0.1105   1.0000
  13.500   1.4972   0.03117   0.02567  -0.0508   0.1048   1.0000
  13.750   1.5089   0.03232   0.02684  -0.0499   0.1005   1.0000
  14.000   1.5211   0.03347   0.02801  -0.0491   0.0969   1.0000
  14.250   1.5299   0.03490   0.02942  -0.0482   0.0919   1.0000
  14.500   1.5412   0.03615   0.03070  -0.0474   0.0878   1.0000
  14.750   1.5511   0.03756   0.03212  -0.0466   0.0839   1.0000
  15.000   1.5587   0.03916   0.03371  -0.0458   0.0789   1.0000
  15.250   1.5695   0.04054   0.03513  -0.0452   0.0762   1.0000
  15.500   1.5780   0.04214   0.03674  -0.0445   0.0724   1.0000
  15.750   1.5844   0.04397   0.03857  -0.0438   0.0681   1.0000
  16.000   1.5940   0.04553   0.04017  -0.0433   0.0657   1.0000
  16.250   1.6014   0.04731   0.04198  -0.0427   0.0624   1.0000
  16.500   1.6057   0.04945   0.04412  -0.0422   0.0586   1.0000
  16.750   1.6138   0.05125   0.04597  -0.0418   0.0560   1.0000
  17.000   1.6185   0.05344   0.04818  -0.0414   0.0529   1.0000
  17.250   1.6215   0.05586   0.05062  -0.0411   0.0495   1.0000
  17.500   1.6275   0.05799   0.05280  -0.0409   0.0471   1.0000
  17.750   1.6300   0.06055   0.05539  -0.0408   0.0445   1.0000
  18.000   1.6313   0.06332   0.05818  -0.0407   0.0413   1.0000
  18.250   1.6343   0.06595   0.06087  -0.0408   0.0392   1.0000
  18.500   1.6327   0.06919   0.06413  -0.0410   0.0363   1.0000
  18.750   1.6328   0.07228   0.06727  -0.0413   0.0339   1.0000
  19.000   1.6314   0.07563   0.07067  -0.0418   0.0315   1.0000
  19.250   1.6271   0.07945   0.07455  -0.0424   0.0294   1.0000
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