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EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 396 AIRFOIL (e396-il)
Reynolds number: 50,000
Max Cl/Cd: 22.72 at α=11.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e396-il-50000-n5.txt
Download as CSV file: xf-e396-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 396 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3085   0.13192   0.12539  -0.0443   1.0000   0.0534
 -10.500  -0.3172   0.12993   0.12348  -0.0428   1.0000   0.0530
 -10.250  -0.3264   0.12792   0.12157  -0.0414   1.0000   0.0524
 -10.000  -0.3252   0.12408   0.11777  -0.0434   0.9972   0.0517
  -9.750  -0.3168   0.11920   0.11290  -0.0477   0.9921   0.0510
  -9.500  -0.3088   0.11457   0.10828  -0.0516   0.9866   0.0511
  -9.000  -0.2940   0.10612   0.09982  -0.0588   0.9748   0.0538
  -8.750  -0.2901   0.10135   0.09507  -0.0630   0.9688   0.0553
  -8.500  -0.2900   0.09661   0.09037  -0.0666   0.9613   0.0562
  -8.250  -0.2917   0.09177   0.08557  -0.0702   0.9540   0.0566
  -8.000  -0.2954   0.08675   0.08059  -0.0741   0.9462   0.0567
  -7.750  -0.3066   0.08176   0.07570  -0.0770   0.9365   0.0568
  -7.500  -0.3119   0.07401   0.06796  -0.0848   0.9283   0.0569
  -7.250  -0.3205   0.06439   0.05821  -0.0956   0.9184   0.0566
  -7.000  -0.3263   0.05525   0.04855  -0.1052   0.9090   0.0577
  -6.750  -0.3062   0.05067   0.04361  -0.1106   0.9038   0.0620
  -6.500  -0.2864   0.04724   0.03979  -0.1137   0.8981   0.0669
  -6.250  -0.2615   0.04278   0.03459  -0.1180   0.8926   0.0733
  -6.000  -0.2294   0.04078   0.03223  -0.1208   0.8889   0.0824
  -5.750  -0.2047   0.03922   0.03044  -0.1219   0.8838   0.0908
  -5.500  -0.1772   0.03747   0.02827  -0.1234   0.8786   0.1010
  -5.250  -0.1434   0.03618   0.02670  -0.1255   0.8750   0.1145
  -5.000  -0.1142   0.03513   0.02538  -0.1266   0.8706   0.1275
  -4.750  -0.0904   0.03455   0.02463  -0.1268   0.8647   0.1419
  -4.500  -0.0576   0.03384   0.02383  -0.1283   0.8608   0.1584
  -4.250  -0.0271   0.03338   0.02328  -0.1294   0.8568   0.1778
  -4.000  -0.0055   0.03310   0.02288  -0.1289   0.8504   0.1947
  -3.750   0.0269   0.03270   0.02238  -0.1302   0.8465   0.2179
  -3.500   0.0582   0.03243   0.02195  -0.1312   0.8425   0.2420
  -3.250   0.0781   0.03243   0.02192  -0.1304   0.8358   0.2617
  -3.000   0.1110   0.03222   0.02160  -0.1316   0.8319   0.2889
  -2.750   0.1395   0.03216   0.02151  -0.1320   0.8274   0.3139
  -2.500   0.1605   0.03231   0.02158  -0.1314   0.8209   0.3370
  -2.250   0.1935   0.03219   0.02141  -0.1324   0.8171   0.3663
  -2.000   0.2185   0.03233   0.02148  -0.1323   0.8118   0.3934
  -1.750   0.2412   0.03251   0.02168  -0.1318   0.8058   0.4193
  -1.500   0.2745   0.03243   0.02155  -0.1327   0.8022   0.4519
  -1.250   0.2936   0.03277   0.02192  -0.1317   0.7957   0.4791
  -1.000   0.3192   0.03293   0.02209  -0.1315   0.7903   0.5111
  -0.750   0.3522   0.03283   0.02201  -0.1322   0.7870   0.5482
  -0.500   0.3654   0.03338   0.02264  -0.1302   0.7793   0.5788
  -0.250   0.3923   0.03344   0.02275  -0.1299   0.7746   0.6199
   0.000   0.4236   0.03325   0.02265  -0.1299   0.7717   0.6670
   0.250   0.4289   0.03398   0.02350  -0.1267   0.7626   0.7077
   0.500   0.4524   0.03379   0.02344  -0.1251   0.7586   0.7701
   0.750   0.4568   0.03419   0.02400  -0.1212   0.7506   0.8526
   1.000   0.4868   0.03424   0.02394  -0.1219   0.7453   1.0000
   1.500   0.5373   0.03556   0.02492  -0.1229   0.7327   1.0000
   1.750   0.5736   0.03574   0.02493  -0.1244   0.7292   1.0000
   2.250   0.6183   0.03719   0.02619  -0.1241   0.7158   1.0000
   2.500   0.6343   0.03820   0.02714  -0.1233   0.7077   1.0000
   2.750   0.6620   0.03868   0.02756  -0.1236   0.7023   1.0000
   3.000   0.6911   0.03909   0.02790  -0.1241   0.6976   1.0000
   3.250   0.7050   0.04021   0.02900  -0.1230   0.6887   1.0000
   3.500   0.7404   0.04027   0.02904  -0.1239   0.6853   1.0000
   3.750   0.7474   0.04178   0.03055  -0.1222   0.6748   1.0000
   4.000   0.7819   0.04183   0.03059  -0.1229   0.6712   1.0000
   4.250   0.7892   0.04336   0.03215  -0.1212   0.6607   1.0000
   4.500   0.8233   0.04338   0.03220  -0.1219   0.6569   1.0000
   4.750   0.8303   0.04496   0.03382  -0.1202   0.6461   1.0000
   5.000   0.8648   0.04489   0.03378  -0.1208   0.6423   1.0000
   5.250   0.8713   0.04654   0.03548  -0.1191   0.6312   1.0000
   5.500   0.9067   0.04633   0.03535  -0.1196   0.6276   1.0000
   5.750   0.9125   0.04804   0.03713  -0.1179   0.6161   1.0000
   6.000   0.9475   0.04775   0.03692  -0.1182   0.6122   1.0000
   6.250   0.9548   0.04937   0.03863  -0.1166   0.6007   1.0000
   6.500   0.9650   0.05081   0.04017  -0.1153   0.5900   1.0000
   6.750   0.9986   0.05042   0.03991  -0.1153   0.5851   1.0000
   7.000   1.0065   0.05202   0.04161  -0.1138   0.5734   1.0000
   7.250   1.0405   0.05144   0.04115  -0.1136   0.5686   1.0000
   7.500   1.0511   0.05278   0.04264  -0.1123   0.5571   1.0000
   7.750   1.0607   0.05422   0.04420  -0.1109   0.5453   1.0000
   8.000   1.0990   0.05294   0.04310  -0.1106   0.5410   1.0000
   8.250   1.1069   0.05447   0.04476  -0.1090   0.5283   1.0000
   8.500   1.1175   0.05574   0.04617  -0.1076   0.5160   1.0000
   8.750   1.1601   0.05370   0.04437  -0.1071   0.5116   1.0000
   9.250   1.1810   0.05599   0.04697  -0.1041   0.4854   1.0000
   9.500   1.1946   0.05681   0.04795  -0.1026   0.4725   1.0000
   9.750   1.2110   0.05726   0.04859  -0.1012   0.4597   1.0000
  10.000   1.2300   0.05737   0.04891  -0.0998   0.4469   1.0000
  10.250   1.2495   0.05736   0.04908  -0.0983   0.4332   1.0000
  10.500   1.2670   0.05751   0.04941  -0.0968   0.4180   1.0000
  10.750   1.2841   0.05769   0.04975  -0.0952   0.4016   1.0000
  11.000   1.3035   0.05757   0.04976  -0.0936   0.3841   1.0000
  11.250   1.3182   0.05801   0.05030  -0.0919   0.3647   1.0000
  11.500   1.3247   0.05949   0.05187  -0.0904   0.3436   1.0000
  11.750   1.3363   0.06031   0.05274  -0.0887   0.3213   1.0000
  12.000   1.3405   0.06214   0.05460  -0.0872   0.2986   1.0000
  12.250   1.3437   0.06418   0.05661  -0.0858   0.2762   1.0000
  12.500   1.3449   0.06653   0.05892  -0.0846   0.2542   1.0000
  12.750   1.3435   0.06940   0.06177  -0.0836   0.2335   1.0000
  13.000   1.3408   0.07253   0.06487  -0.0828   0.2137   1.0000
  13.250   1.3383   0.07573   0.06797  -0.0821   0.1956   1.0000
  13.500   1.3341   0.07940   0.07168  -0.0818   0.1782   1.0000
  13.750   1.3299   0.08317   0.07546  -0.0817   0.1621   1.0000
  14.000   1.3261   0.08698   0.07927  -0.0817   0.1475   1.0000
  14.250   1.3222   0.09093   0.08322  -0.0819   0.1341   1.0000
  14.500   1.3183   0.09496   0.08725  -0.0822   0.1218   1.0000
  14.750   1.3153   0.09890   0.09125  -0.0827   0.1112   1.0000
  15.000   1.3124   0.10287   0.09518  -0.0833   0.1016   1.0000
  15.250   1.3103   0.10702   0.09947  -0.0840   0.0923   1.0000
  15.500   1.3091   0.11094   0.10346  -0.0847   0.0847   1.0000
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