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E182 (8.47%) (e182-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E182 (8.47%) (e182-il)
Reynolds number: 50,000
Max Cl/Cd: 32.83 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e182-il-50000.txt
Download as CSV file: xf-e182-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E182 (8.47%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5750   0.12236   0.11603   0.0233   1.0000   0.2065
  -9.250  -0.5568   0.11696   0.11063   0.0239   1.0000   0.2139
  -9.000  -0.5760   0.11606   0.10986   0.0201   1.0000   0.2215
  -8.750  -0.5509   0.11019   0.10396   0.0216   1.0000   0.2326
  -8.500  -0.5446   0.10622   0.10004   0.0209   1.0000   0.2413
  -8.250  -0.5588   0.10437   0.09833   0.0180   1.0000   0.2510
  -8.000  -0.5536   0.10090   0.09491   0.0176   1.0000   0.2642
  -7.750  -0.5393   0.09652   0.09054   0.0181   1.0000   0.2774
  -7.500  -0.5326   0.09279   0.08683   0.0180   1.0000   0.2912
  -7.250  -0.5278   0.08939   0.08350   0.0177   1.0000   0.3056
  -7.000  -0.5399   0.08709   0.08135   0.0163   1.0000   0.3221
  -6.500  -0.5106   0.07922   0.07354   0.0189   1.0000   0.3630
  -6.250  -0.4975   0.07566   0.07003   0.0205   1.0000   0.3896
  -5.750  -0.4987   0.05195   0.04509  -0.0223   1.0000   0.1345
  -5.500  -0.4799   0.04646   0.03915  -0.0234   1.0000   0.1186
  -5.250  -0.4611   0.04181   0.03357  -0.0238   1.0000   0.1080
  -5.000  -0.4410   0.03836   0.02975  -0.0234   1.0000   0.1073
  -4.750  -0.4215   0.03544   0.02634  -0.0226   1.0000   0.1078
  -4.500  -0.4032   0.03292   0.02337  -0.0212   1.0000   0.1083
  -4.250  -0.3874   0.03046   0.02067  -0.0195   1.0000   0.1093
  -4.000  -0.3719   0.02844   0.01851  -0.0176   1.0000   0.1120
  -3.750  -0.3553   0.02677   0.01662  -0.0158   1.0000   0.1168
  -3.500  -0.3379   0.02524   0.01495  -0.0141   1.0000   0.1285
  -3.250  -0.3184   0.02376   0.01334  -0.0126   1.0000   0.1482
  -3.000  -0.1212   0.01643   0.00916  -0.0330   1.0000   1.0000
  -2.750  -0.1262   0.01643   0.00892  -0.0299   1.0000   1.0000
  -2.500  -0.1336   0.01661   0.00885  -0.0258   1.0000   1.0000
  -2.250  -0.1347   0.01680   0.00876  -0.0224   1.0000   1.0000
  -2.000  -0.1312   0.01702   0.00868  -0.0195   1.0000   1.0000
  -1.750  -0.1246   0.01725   0.00863  -0.0171   1.0000   1.0000
  -1.500  -0.1157   0.01751   0.00861  -0.0151   1.0000   1.0000
  -1.250  -0.1048   0.01779   0.00864  -0.0133   1.0000   1.0000
  -1.000  -0.0923   0.01809   0.00867  -0.0118   1.0000   1.0000
  -0.750  -0.0788   0.01843   0.00878  -0.0106   1.0000   1.0000
  -0.500  -0.0645   0.01879   0.00895  -0.0095   1.0000   1.0000
  -0.250  -0.0272   0.01940   0.00933  -0.0128   0.9918   1.0000
   0.000   0.0149   0.02011   0.00983  -0.0169   0.9820   1.0000
   0.250   0.0579   0.02086   0.01042  -0.0211   0.9719   1.0000
   0.500   0.0940   0.02154   0.01098  -0.0240   0.9614   1.0000
   0.750   0.1302   0.02227   0.01162  -0.0269   0.9512   1.0000
   1.000   0.1684   0.02304   0.01233  -0.0300   0.9413   1.0000
   1.250   0.2075   0.02385   0.01310  -0.0332   0.9310   1.0000
   1.500   0.2366   0.02460   0.01384  -0.0346   0.9199   1.0000
   1.750   0.2669   0.02540   0.01466  -0.0362   0.9090   1.0000
   2.000   0.2997   0.02625   0.01553  -0.0381   0.8978   1.0000
   2.250   0.3352   0.02711   0.01645  -0.0404   0.8861   1.0000
   2.500   0.3731   0.02797   0.01744  -0.0430   0.8737   1.0000
   2.750   0.4070   0.02882   0.01840  -0.0448   0.8605   1.0000
   3.000   0.4388   0.02967   0.01937  -0.0460   0.8464   1.0000
   3.250   0.4698   0.03051   0.02035  -0.0469   0.8315   1.0000
   3.500   0.4931   0.03140   0.02141  -0.0465   0.8152   1.0000
   3.750   0.5179   0.03224   0.02241  -0.0461   0.7974   1.0000
   4.000   0.5506   0.03288   0.02326  -0.0463   0.7784   1.0000
   4.250   0.5827   0.03338   0.02399  -0.0458   0.7581   1.0000
   4.500   0.6095   0.03379   0.02468  -0.0443   0.7356   1.0000
   4.750   0.6365   0.03397   0.02511  -0.0422   0.7115   1.0000
   5.000   0.6682   0.03345   0.02487  -0.0392   0.6865   1.0000
   5.250   0.6978   0.03242   0.02416  -0.0350   0.6602   1.0000
   5.500   0.7208   0.03144   0.02345  -0.0303   0.6293   1.0000
   5.750   0.7441   0.02992   0.02220  -0.0250   0.5942   1.0000
   6.000   0.7681   0.02743   0.01994  -0.0184   0.5513   1.0000
   6.250   0.7883   0.02433   0.01692  -0.0109   0.4785   1.0000
   6.500   0.7915   0.02411   0.01538  -0.0042   0.3020   1.0000
   6.750   0.7890   0.02799   0.01781  -0.0011   0.1741   1.0000
   7.000   0.8029   0.03105   0.02025   0.0012   0.1254   1.0000
   7.250   0.8300   0.03365   0.02287   0.0030   0.1076   1.0000
   7.500   0.8561   0.03640   0.02563   0.0041   0.0973   1.0000
   7.750   0.8793   0.03900   0.02848   0.0051   0.0898   1.0000
   8.000   0.9019   0.04264   0.03230   0.0059   0.0862   1.0000
   8.250   0.9200   0.04627   0.03647   0.0071   0.0855   1.0000
   8.500   0.9347   0.05026   0.04093   0.0081   0.0855   1.0000
   8.750   0.9464   0.05466   0.04574   0.0090   0.0861   1.0000
   9.000   0.9556   0.05896   0.05046   0.0099   0.0873   1.0000
   9.250   0.9381   0.06377   0.05614   0.0108   0.0907   1.0000
   9.500   0.9227   0.06894   0.06169   0.0108   0.0933   1.0000
   9.750   0.9070   0.07390   0.06686   0.0104   0.0954   1.0000
  10.000   0.8908   0.07871   0.07176   0.0099   0.0972   1.0000
  10.250   0.8994   0.08391   0.07701   0.0098   0.1002   1.0000
  10.500   0.8415   0.09101   0.08419   0.0029   0.1019   1.0000
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