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EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1200 AIRFOIL (e1200-il)
Reynolds number: 500,000
Max Cl/Cd: 96.07 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1200-il-500000-n5.txt
Download as CSV file: xf-e1200-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.5993   0.09179   0.08875  -0.0780   1.0000   0.0133
 -15.750  -0.6479   0.07813   0.07484  -0.0865   0.9997   0.0132
 -15.500  -0.6698   0.06874   0.06524  -0.0936   0.9919   0.0132
 -15.250  -0.6831   0.06130   0.05760  -0.1001   0.9810   0.0132
 -15.000  -0.6874   0.05464   0.05070  -0.1073   0.9578   0.0133
 -14.750  -0.6752   0.04891   0.04472  -0.1162   0.9439   0.0134
 -14.500  -0.6557   0.04388   0.03938  -0.1253   0.9302   0.0136
 -14.250  -0.6314   0.04010   0.03533  -0.1329   0.9120   0.0136
 -14.000  -0.6184   0.03739   0.03231  -0.1364   0.8875   0.0138
 -13.750  -0.6142   0.03545   0.03014  -0.1368   0.8680   0.0139
 -13.500  -0.6124   0.03359   0.02812  -0.1363   0.8538   0.0140
 -13.000  -0.6031   0.03069   0.02498  -0.1347   0.8329   0.0144
 -12.750  -0.5967   0.02943   0.02360  -0.1338   0.8246   0.0145
 -12.500  -0.5885   0.02829   0.02237  -0.1329   0.8172   0.0146
 -12.250  -0.5796   0.02728   0.02126  -0.1319   0.8107   0.0149
 -12.000  -0.5702   0.02621   0.02009  -0.1308   0.8053   0.0150
 -11.750  -0.5596   0.02526   0.01907  -0.1297   0.7999   0.0152
 -11.500  -0.5487   0.02432   0.01803  -0.1285   0.7950   0.0153
 -11.250  -0.5369   0.02348   0.01709  -0.1274   0.7909   0.0155
 -11.000  -0.5246   0.02262   0.01615  -0.1262   0.7866   0.0156
 -10.750  -0.5117   0.02185   0.01530  -0.1249   0.7824   0.0158
 -10.500  -0.4987   0.02112   0.01448  -0.1236   0.7783   0.0160
 -10.250  -0.4853   0.02044   0.01371  -0.1222   0.7748   0.0164
 -10.000  -0.4720   0.01975   0.01297  -0.1207   0.7715   0.0166
  -9.750  -0.4594   0.01915   0.01230  -0.1189   0.7681   0.0167
  -9.500  -0.4469   0.01866   0.01173  -0.1171   0.7649   0.0169
  -9.250  -0.4305   0.01820   0.01119  -0.1157   0.7621   0.0171
  -9.000  -0.4152   0.01756   0.01049  -0.1143   0.7595   0.0174
  -8.750  -0.3981   0.01698   0.00989  -0.1131   0.7568   0.0177
  -8.500  -0.3791   0.01648   0.00937  -0.1121   0.7539   0.0181
  -8.250  -0.3589   0.01603   0.00890  -0.1113   0.7512   0.0185
  -8.000  -0.3373   0.01566   0.00848  -0.1106   0.7488   0.0191
  -7.750  -0.3154   0.01527   0.00806  -0.1100   0.7466   0.0196
  -7.500  -0.2928   0.01492   0.00765  -0.1094   0.7445   0.0202
  -7.250  -0.2694   0.01461   0.00727  -0.1090   0.7424   0.0207
  -7.000  -0.2464   0.01422   0.00687  -0.1085   0.7402   0.0212
  -6.750  -0.2232   0.01383   0.00647  -0.1080   0.7378   0.0219
  -6.500  -0.1990   0.01350   0.00612  -0.1077   0.7356   0.0227
  -6.250  -0.1741   0.01322   0.00582  -0.1074   0.7335   0.0236
  -6.000  -0.1487   0.01296   0.00553  -0.1072   0.7315   0.0246
  -5.750  -0.1231   0.01271   0.00524  -0.1070   0.7296   0.0260
  -5.500  -0.0974   0.01245   0.00497  -0.1069   0.7276   0.0282
  -5.250  -0.0713   0.01222   0.00472  -0.1068   0.7257   0.0315
  -5.000  -0.0455   0.01194   0.00450  -0.1067   0.7237   0.0384
  -4.750  -0.0196   0.01164   0.00428  -0.1067   0.7218   0.0537
  -4.500   0.0065   0.01136   0.00408  -0.1067   0.7198   0.0725
  -4.250   0.0329   0.01108   0.00390  -0.1067   0.7177   0.0958
  -4.000   0.0595   0.01081   0.00373  -0.1068   0.7156   0.1231
  -3.750   0.0864   0.01055   0.00357  -0.1069   0.7136   0.1537
  -3.500   0.1132   0.01024   0.00340  -0.1071   0.7119   0.1961
  -3.250   0.1403   0.00989   0.00324  -0.1074   0.7102   0.2526
  -3.000   0.1667   0.00943   0.00306  -0.1077   0.7083   0.3289
  -2.750   0.1929   0.00886   0.00288  -0.1081   0.7062   0.4333
  -2.500   0.2200   0.00847   0.00285  -0.1083   0.7041   0.5339
  -2.250   0.2484   0.00840   0.00291  -0.1085   0.7020   0.5787
  -2.000   0.2773   0.00841   0.00293  -0.1087   0.6999   0.6011
  -1.750   0.3064   0.00844   0.00294  -0.1090   0.6978   0.6137
  -1.500   0.3356   0.00847   0.00295  -0.1093   0.6959   0.6232
  -1.250   0.3652   0.00853   0.00295  -0.1096   0.6938   0.6327
  -1.000   0.3936   0.00856   0.00301  -0.1097   0.6913   0.6409
  -0.750   0.4222   0.00860   0.00304  -0.1099   0.6882   0.6509
  -0.500   0.4503   0.00863   0.00310  -0.1099   0.6844   0.6602
  -0.250   0.4790   0.00867   0.00308  -0.1101   0.6803   0.6678
   0.000   0.5071   0.00869   0.00310  -0.1101   0.6760   0.6726
   0.250   0.5347   0.00869   0.00311  -0.1101   0.6701   0.6765
   0.500   0.5627   0.00869   0.00307  -0.1101   0.6641   0.6797
   0.750   0.5908   0.00871   0.00305  -0.1102   0.6585   0.6826
   1.000   0.6186   0.00872   0.00306  -0.1103   0.6528   0.6850
   1.250   0.6463   0.00873   0.00307  -0.1103   0.6477   0.6871
   1.500   0.6740   0.00876   0.00310  -0.1103   0.6426   0.6896
   1.750   0.7015   0.00879   0.00314  -0.1103   0.6366   0.6922
   2.000   0.7288   0.00883   0.00315  -0.1103   0.6306   0.6947
   2.250   0.7562   0.00887   0.00320  -0.1103   0.6235   0.6971
   2.500   0.7829   0.00892   0.00322  -0.1101   0.6156   0.6997
   2.750   0.8096   0.00897   0.00328  -0.1100   0.6068   0.7021
   3.000   0.8351   0.00904   0.00333  -0.1096   0.5965   0.7043
   3.250   0.8597   0.00913   0.00340  -0.1090   0.5835   0.7065
   3.500   0.8835   0.00926   0.00349  -0.1083   0.5679   0.7088
   3.750   0.9059   0.00943   0.00359  -0.1073   0.5485   0.7115
   4.000   0.9252   0.00970   0.00375  -0.1058   0.5227   0.7144
   4.250   0.9426   0.01004   0.00395  -0.1040   0.4951   0.7171
   4.500   0.9573   0.01043   0.00421  -0.1016   0.4667   0.7194
   4.750   0.9695   0.01086   0.00452  -0.0988   0.4385   0.7218
   5.000   0.9793   0.01127   0.00484  -0.0956   0.4130   0.7245
   5.250   0.9899   0.01172   0.00519  -0.0926   0.3915   0.7276
   5.500   1.0016   0.01219   0.00557  -0.0899   0.3701   0.7308
   5.750   1.0136   0.01269   0.00598  -0.0873   0.3502   0.7338
   6.000   1.0260   0.01318   0.00642  -0.0849   0.3328   0.7365
   6.250   1.0387   0.01368   0.00687  -0.0826   0.3171   0.7392
   6.500   1.0509   0.01423   0.00737  -0.0803   0.3011   0.7424
   6.750   1.0641   0.01477   0.00788  -0.0783   0.2881   0.7461
   7.000   1.0776   0.01534   0.00841  -0.0763   0.2770   0.7496
   7.250   1.0913   0.01591   0.00896  -0.0745   0.2655   0.7528
   7.500   1.1052   0.01650   0.00954  -0.0728   0.2547   0.7561
   7.750   1.1187   0.01713   0.01016  -0.0711   0.2456   0.7597
   8.000   1.1336   0.01774   0.01077  -0.0696   0.2368   0.7636
   8.250   1.1475   0.01842   0.01144  -0.0681   0.2283   0.7677
   8.500   1.1619   0.01907   0.01210  -0.0667   0.2202   0.7719
   8.750   1.1761   0.01975   0.01280  -0.0653   0.2138   0.7765
   9.000   1.1912   0.02043   0.01349  -0.0640   0.2065   0.7812
   9.250   1.2044   0.02121   0.01428  -0.0626   0.2000   0.7859
   9.500   1.2197   0.02188   0.01499  -0.0614   0.1935   0.7909
   9.750   1.2326   0.02271   0.01583  -0.0601   0.1869   0.7967
  10.000   1.2476   0.02344   0.01660  -0.0590   0.1813   0.8029
  10.250   1.2614   0.02423   0.01743  -0.0578   0.1754   0.8100
  10.750   1.2887   0.02588   0.01916  -0.0555   0.1647   0.8264
  11.000   1.3015   0.02677   0.02009  -0.0543   0.1590   0.8361
  11.250   1.3139   0.02767   0.02105  -0.0530   0.1543   0.8482
  11.500   1.3268   0.02849   0.02195  -0.0518   0.1495   0.8636
  11.750   1.3364   0.02943   0.02297  -0.0502   0.1440   0.8897
  12.250   1.3644   0.03130   0.02499  -0.0488   0.1344   1.0000
  12.500   1.3759   0.03250   0.02619  -0.0479   0.1297   1.0000
  12.750   1.3889   0.03361   0.02732  -0.0472   0.1249   1.0000
  13.000   1.3998   0.03489   0.02859  -0.0464   0.1183   1.0000
  13.250   1.4105   0.03622   0.02993  -0.0456   0.1136   1.0000
  13.500   1.4219   0.03752   0.03124  -0.0449   0.1074   1.0000
  13.750   1.4303   0.03909   0.03279  -0.0441   0.1019   1.0000
  14.000   1.4419   0.04041   0.03415  -0.0435   0.0971   1.0000
  14.250   1.4499   0.04206   0.03580  -0.0428   0.0917   1.0000
  14.500   1.4601   0.04357   0.03734  -0.0422   0.0882   1.0000
  14.750   1.4695   0.04516   0.03898  -0.0417   0.0842   1.0000
  15.000   1.4772   0.04695   0.04077  -0.0411   0.0803   1.0000
  15.250   1.4853   0.04872   0.04258  -0.0407   0.0767   1.0000
  15.500   1.4931   0.05056   0.04447  -0.0403   0.0728   1.0000
  15.750   1.4985   0.05269   0.04661  -0.0399   0.0689   1.0000
  16.000   1.5054   0.05470   0.04866  -0.0396   0.0654   1.0000
  16.250   1.5115   0.05683   0.05085  -0.0393   0.0623   1.0000
  16.500   1.5150   0.05929   0.05333  -0.0392   0.0590   1.0000
  16.750   1.5200   0.06164   0.05574  -0.0391   0.0563   1.0000
  17.000   1.5245   0.06409   0.05825  -0.0391   0.0534   1.0000
  17.250   1.5256   0.06699   0.06119  -0.0392   0.0504   1.0000
  17.500   1.5279   0.06981   0.06407  -0.0394   0.0478   1.0000
  17.750   1.5301   0.07269   0.06702  -0.0397   0.0454   1.0000
  18.000   1.5297   0.07598   0.07037  -0.0402   0.0429   1.0000
  18.250   1.5292   0.07934   0.07380  -0.0408   0.0410   1.0000
  18.500   1.5291   0.08273   0.07728  -0.0415   0.0391   1.0000
  18.750   1.5265   0.08651   0.08113  -0.0424   0.0369   1.0000
  19.000   1.5219   0.09064   0.08533  -0.0435   0.0351   1.0000
  19.250   1.5189   0.09462   0.08940  -0.0447   0.0331   1.0000
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