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EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 433 AIRFOIL (e433-il)
Reynolds number: 500,000
Max Cl/Cd: 116.11 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e433-il-500000.txt
Download as CSV file: xf-e433-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 433 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  -0.0990   0.03000   0.02708  -0.1477   0.9012   0.0190
  -8.250  -0.1090   0.02800   0.02499  -0.1453   0.8929   0.0191
  -8.000  -0.1070   0.02592   0.02281  -0.1442   0.8872   0.0193
  -7.750  -0.1058   0.02399   0.02080  -0.1426   0.8810   0.0196
  -7.500  -0.1008   0.02208   0.01877  -0.1413   0.8756   0.0202
  -7.250  -0.0942   0.01963   0.01609  -0.1402   0.8711   0.0212
  -7.000  -0.0939   0.01809   0.01391  -0.1364   0.8644   0.0233
  -6.750  -0.1042   0.02018   0.01465  -0.1390   0.8690   0.0119
  -6.500  -0.0844   0.01860   0.01282  -0.1378   0.8646   0.0119
  -6.250  -0.0604   0.01746   0.01144  -0.1372   0.8609   0.0117
  -6.000  -0.0358   0.01620   0.01005  -0.1370   0.8578   0.0120
  -5.750  -0.0108   0.01566   0.00949  -0.1368   0.8545   0.0130
  -5.500   0.0123   0.01502   0.00877  -0.1361   0.8504   0.0135
  -5.250   0.0367   0.01423   0.00788  -0.1355   0.8468   0.0138
  -5.000   0.0618   0.01348   0.00704  -0.1351   0.8436   0.0139
  -4.750   0.0878   0.01286   0.00633  -0.1349   0.8405   0.0142
  -4.500   0.1100   0.01240   0.00584  -0.1340   0.8366   0.0147
  -4.250   0.1333   0.01177   0.00518  -0.1334   0.8327   0.0157
  -4.000   0.1600   0.01140   0.00477  -0.1334   0.8294   0.0184
  -3.750   0.1870   0.01089   0.00426  -0.1334   0.8264   0.0298
  -3.500   0.2108   0.01033   0.00398  -0.1331   0.8228   0.0888
  -3.250   0.2352   0.00983   0.00380  -0.1331   0.8188   0.1721
  -3.000   0.2601   0.00890   0.00355  -0.1336   0.8152   0.3668
  -2.750   0.2854   0.00793   0.00355  -0.1339   0.8121   0.6602
  -2.500   0.3132   0.00803   0.00365  -0.1338   0.8088   0.7020
  -2.250   0.3396   0.00812   0.00371  -0.1334   0.8047   0.7217
  -2.000   0.3674   0.00823   0.00376  -0.1333   0.8008   0.7373
  -1.750   0.3959   0.00835   0.00384  -0.1332   0.7974   0.7504
  -1.500   0.4237   0.00848   0.00393  -0.1331   0.7940   0.7592
  -1.250   0.4500   0.00857   0.00397  -0.1328   0.7895   0.7681
  -1.000   0.4761   0.00864   0.00405  -0.1322   0.7853   0.7748
  -0.750   0.5044   0.00876   0.00411  -0.1322   0.7816   0.7851
  -0.500   0.5286   0.00895   0.00432  -0.1311   0.7774   0.7950
  -0.250   0.5535   0.00901   0.00439  -0.1303   0.7725   0.8022
   0.000   0.5807   0.00904   0.00438  -0.1301   0.7682   0.8061
   0.250   0.6104   0.00906   0.00434  -0.1306   0.7644   0.8093
   0.500   0.6363   0.00905   0.00432  -0.1305   0.7591   0.8124
   0.750   0.6650   0.00902   0.00425  -0.1308   0.7541   0.8149
   1.250   0.7185   0.00898   0.00420  -0.1306   0.7439   0.8187
   1.500   0.7458   0.00897   0.00416  -0.1306   0.7384   0.8209
   1.750   0.7741   0.00897   0.00414  -0.1309   0.7334   0.8230
   2.000   0.7998   0.00897   0.00415  -0.1306   0.7268   0.8255
   2.250   0.8285   0.00897   0.00411  -0.1310   0.7211   0.8280
   2.500   0.8545   0.00898   0.00413  -0.1308   0.7141   0.8304
   2.750   0.8805   0.00897   0.00411  -0.1305   0.7073   0.8322
   3.000   0.9056   0.00898   0.00415  -0.1301   0.7000   0.8341
   3.250   0.9312   0.00900   0.00417  -0.1298   0.6922   0.8363
   3.500   0.9560   0.00904   0.00422  -0.1293   0.6838   0.8389
   3.750   0.9822   0.00910   0.00425  -0.1292   0.6753   0.8416
   4.000   1.0064   0.00915   0.00432  -0.1286   0.6652   0.8442
   4.250   1.0304   0.00920   0.00438  -0.1280   0.6550   0.8464
   4.500   1.0534   0.00927   0.00445  -0.1272   0.6442   0.8486
   4.750   1.0751   0.00936   0.00454  -0.1261   0.6315   0.8511
   5.000   1.0963   0.00947   0.00465  -0.1249   0.6177   0.8540
   5.250   1.1170   0.00962   0.00478  -0.1236   0.6025   0.8573
   5.500   1.1367   0.00981   0.00493  -0.1222   0.5857   0.8604
   5.750   1.1532   0.00998   0.00509  -0.1201   0.5675   0.8632
   6.000   1.1669   0.01019   0.00526  -0.1174   0.5476   0.8666
   6.250   1.1791   0.01048   0.00550  -0.1145   0.5267   0.8704
   6.500   1.1920   0.01084   0.00580  -0.1118   0.5040   0.8744
   6.750   1.2030   0.01123   0.00613  -0.1088   0.4819   0.8783
   7.000   1.2131   0.01168   0.00651  -0.1057   0.4585   0.8829
   7.250   1.2238   0.01218   0.00694  -0.1028   0.4355   0.8879
   7.500   1.2340   0.01269   0.00740  -0.0999   0.4126   0.8926
   7.750   1.2425   0.01327   0.00791  -0.0968   0.3893   0.8980
   8.000   1.2534   0.01387   0.00845  -0.0943   0.3675   0.9040
   8.250   1.2617   0.01447   0.00902  -0.0912   0.3456   0.9106
   8.500   1.2708   0.01516   0.00965  -0.0885   0.3247   0.9188
   8.750   1.2781   0.01580   0.01027  -0.0855   0.3034   0.9291
   9.000   1.2849   0.01648   0.01093  -0.0824   0.2841   0.9453
   9.250   1.2972   0.01722   0.01164  -0.0807   0.2629   1.0000
   9.500   1.3100   0.01818   0.01250  -0.0794   0.2407   1.0000
   9.750   1.3217   0.01920   0.01344  -0.0778   0.2195   1.0000
  10.000   1.3334   0.02022   0.01438  -0.0763   0.1993   1.0000
  10.250   1.3439   0.02132   0.01539  -0.0747   0.1806   1.0000
  10.500   1.3543   0.02244   0.01644  -0.0731   0.1637   1.0000
  10.750   1.3650   0.02355   0.01750  -0.0716   0.1479   1.0000
  11.000   1.3749   0.02472   0.01863  -0.0701   0.1326   1.0000
  11.250   1.3842   0.02597   0.01983  -0.0685   0.1180   1.0000
  11.500   1.3930   0.02727   0.02110  -0.0669   0.1047   1.0000
  11.750   1.4015   0.02862   0.02241  -0.0654   0.0928   1.0000
  12.000   1.4092   0.03007   0.02382  -0.0639   0.0812   1.0000
  12.250   1.4162   0.03161   0.02533  -0.0624   0.0704   1.0000
  12.500   1.4223   0.03325   0.02695  -0.0610   0.0612   1.0000
  12.750   1.4292   0.03488   0.02858  -0.0596   0.0533   1.0000
  13.000   1.4360   0.03656   0.03027  -0.0584   0.0464   1.0000
  13.250   1.4413   0.03841   0.03213  -0.0572   0.0404   1.0000
  13.500   1.4455   0.04042   0.03413  -0.0560   0.0349   1.0000
  13.750   1.4523   0.04223   0.03600  -0.0550   0.0310   1.0000
  14.000   1.4544   0.04455   0.03833  -0.0539   0.0273   1.0000
  14.250   1.4623   0.04634   0.04019  -0.0533   0.0242   1.0000
  14.500   1.4638   0.04886   0.04274  -0.0524   0.0217   1.0000
  14.750   1.4708   0.05084   0.04480  -0.0519   0.0195   1.0000
  15.000   1.4728   0.05343   0.04744  -0.0513   0.0177   1.0000
  15.250   1.4764   0.05591   0.05001  -0.0509   0.0162   1.0000
  15.500   1.4795   0.05850   0.05269  -0.0506   0.0149   1.0000
  15.750   1.4785   0.06165   0.05591  -0.0504   0.0136   1.0000
  16.000   1.4806   0.06451   0.05887  -0.0503   0.0126   1.0000
  16.250   1.4819   0.06754   0.06200  -0.0504   0.0114   1.0000
  16.500   1.4780   0.07135   0.06588  -0.0507   0.0104   1.0000
  16.750   1.4787   0.07462   0.06928  -0.0510   0.0095   1.0000
  17.000   1.4773   0.07825   0.07301  -0.0516   0.0085   1.0000
  17.250   1.4700   0.08285   0.07771  -0.0525   0.0078   1.0000
  17.500   1.4687   0.08666   0.08165  -0.0534   0.0069   1.0000
  17.750   1.4636   0.09113   0.08622  -0.0546   0.0062   1.0000
  18.000   1.4538   0.09649   0.09170  -0.0562   0.0055   1.0000
  18.250   1.4476   0.10135   0.09670  -0.0578   0.0049   1.0000
  18.500   1.4392   0.10668   0.10214  -0.0598   0.0044   1.0000
  18.750   1.4235   0.11341   0.10900  -0.0626   0.0041   1.0000
  19.000   1.4158   0.11885   0.11459  -0.0650   0.0036   1.0000
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