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EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 393 AIRFOIL (e393-il)
Reynolds number: 100,000
Max Cl/Cd: 61.98 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e393-il-100000-n5.txt
Download as CSV file: xf-e393-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 393 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3338   0.09071   0.08610  -0.0464   1.0000   0.0239
  -8.500  -0.3432   0.08739   0.08289  -0.0463   1.0000   0.0237
  -8.000  -0.3718   0.07766   0.07337  -0.0494   0.9963   0.0221
  -7.750  -0.3606   0.07090   0.06662  -0.0580   0.9852   0.0219
  -7.500  -0.3474   0.05882   0.05435  -0.0760   0.9704   0.0220
  -7.250  -0.3347   0.05067   0.04578  -0.0869   0.9566   0.0221
  -6.750  -0.2964   0.04177   0.03636  -0.0961   0.9343   0.0240
  -6.500  -0.2697   0.03678   0.03078  -0.1006   0.9261   0.0243
  -6.250  -0.2410   0.03271   0.02610  -0.1036   0.9178   0.0247
  -6.000  -0.2119   0.02959   0.02244  -0.1055   0.9092   0.0255
  -5.750  -0.1786   0.02691   0.01927  -0.1075   0.9028   0.0267
  -5.500  -0.1484   0.02480   0.01676  -0.1084   0.8940   0.0282
  -5.250  -0.1139   0.02305   0.01466  -0.1100   0.8878   0.0319
  -5.000  -0.0848   0.02188   0.01339  -0.1106   0.8783   0.0357
  -4.750  -0.0516   0.02056   0.01185  -0.1116   0.8714   0.0398
  -4.500  -0.0218   0.01958   0.01082  -0.1123   0.8622   0.0472
  -4.250   0.0087   0.01863   0.00974  -0.1129   0.8537   0.0557
  -4.000   0.0406   0.01780   0.00887  -0.1139   0.8459   0.0709
  -3.750   0.0699   0.01705   0.00809  -0.1144   0.8365   0.0953
  -3.500   0.1013   0.01626   0.00746  -0.1155   0.8290   0.1485
  -3.250   0.1297   0.01549   0.00706  -0.1162   0.8199   0.2432
  -3.000   0.1581   0.01488   0.00688  -0.1167   0.8116   0.3702
  -2.750   0.1869   0.01464   0.00679  -0.1168   0.8037   0.4585
  -2.500   0.2140   0.01458   0.00671  -0.1164   0.7951   0.5161
  -2.250   0.2429   0.01451   0.00660  -0.1163   0.7880   0.5601
  -2.000   0.2691   0.01452   0.00656  -0.1158   0.7793   0.5949
  -1.750   0.2974   0.01449   0.00645  -0.1155   0.7727   0.6267
  -1.500   0.3229   0.01450   0.00643  -0.1148   0.7643   0.6544
  -1.250   0.3499   0.01448   0.00635  -0.1143   0.7578   0.6806
  -1.000   0.3752   0.01450   0.00636  -0.1136   0.7499   0.7056
  -0.750   0.4020   0.01450   0.00628  -0.1131   0.7438   0.7308
  -0.500   0.4263   0.01452   0.00631  -0.1122   0.7361   0.7551
   0.000   0.4753   0.01454   0.00629  -0.1103   0.7229   0.8051
   0.250   0.4999   0.01452   0.00624  -0.1093   0.7172   0.8331
   0.500   0.5220   0.01452   0.00627  -0.1079   0.7102   0.8660
   0.750   0.5481   0.01447   0.00621  -0.1073   0.7043   0.9094
   1.000   0.5840   0.01444   0.00616  -0.1090   0.6979   1.0000
   1.250   0.6134   0.01462   0.00624  -0.1097   0.6915   1.0000
   1.500   0.6432   0.01480   0.00631  -0.1103   0.6859   1.0000
   1.750   0.6708   0.01502   0.00651  -0.1106   0.6790   1.0000
   2.000   0.7006   0.01519   0.00659  -0.1111   0.6739   1.0000
   2.250   0.7271   0.01544   0.00684  -0.1111   0.6668   1.0000
   2.500   0.7557   0.01564   0.00699  -0.1114   0.6612   1.0000
   2.750   0.7828   0.01589   0.00726  -0.1115   0.6548   1.0000
   3.000   0.8102   0.01612   0.00749  -0.1115   0.6485   1.0000
   3.250   0.8381   0.01634   0.00770  -0.1116   0.6426   1.0000
   3.500   0.8642   0.01661   0.00801  -0.1115   0.6356   1.0000
   3.750   0.8927   0.01680   0.00822  -0.1116   0.6298   1.0000
   4.000   0.9176   0.01709   0.00859  -0.1113   0.6217   1.0000
   4.250   0.9455   0.01727   0.00878  -0.1113   0.6150   1.0000
   4.500   0.9703   0.01753   0.00912  -0.1108   0.6062   1.0000
   4.750   0.9964   0.01774   0.00943  -0.1105   0.5980   1.0000
   5.000   1.0227   0.01792   0.00967  -0.1102   0.5894   1.0000
   5.250   1.0469   0.01817   0.01002  -0.1096   0.5792   1.0000
   5.500   1.0721   0.01835   0.01028  -0.1091   0.5691   1.0000
   5.750   1.0979   0.01849   0.01051  -0.1086   0.5588   1.0000
   6.000   1.1214   0.01869   0.01082  -0.1078   0.5464   1.0000
   6.250   1.1445   0.01889   0.01113  -0.1069   0.5330   1.0000
   6.500   1.1673   0.01909   0.01144  -0.1060   0.5186   1.0000
   6.750   1.1899   0.01929   0.01173  -0.1049   0.5030   1.0000
   7.000   1.2105   0.01957   0.01217  -0.1036   0.4844   1.0000
   7.250   1.2304   0.01985   0.01253  -0.1022   0.4634   1.0000
   7.500   1.2490   0.02020   0.01296  -0.1006   0.4388   1.0000
   7.750   1.2659   0.02064   0.01342  -0.0987   0.4098   1.0000
   8.000   1.2801   0.02123   0.01395  -0.0965   0.3743   1.0000
   8.250   1.2902   0.02207   0.01463  -0.0938   0.3321   1.0000
   8.500   1.2961   0.02318   0.01558  -0.0906   0.2892   1.0000
   8.750   1.2978   0.02446   0.01666  -0.0870   0.2514   1.0000
   9.000   1.2989   0.02586   0.01792  -0.0835   0.2186   1.0000
   9.250   1.2994   0.02739   0.01933  -0.0803   0.1887   1.0000
   9.500   1.3000   0.02904   0.02088  -0.0774   0.1635   1.0000
   9.750   1.3003   0.03083   0.02259  -0.0747   0.1410   1.0000
  10.000   1.3015   0.03268   0.02441  -0.0724   0.1209   1.0000
  10.250   1.3014   0.03476   0.02643  -0.0703   0.1029   1.0000
  10.500   1.3014   0.03696   0.02858  -0.0685   0.0858   1.0000
  10.750   1.3018   0.03925   0.03083  -0.0669   0.0695   1.0000
  11.000   1.3017   0.04171   0.03325  -0.0656   0.0560   1.0000
  11.250   1.3015   0.04429   0.03588  -0.0644   0.0456   1.0000
  11.500   1.3003   0.04708   0.03870  -0.0633   0.0378   1.0000
  11.750   1.2975   0.05016   0.04180  -0.0624   0.0323   1.0000
  12.000   1.2968   0.05311   0.04489  -0.0617   0.0279   1.0000
  12.250   1.2949   0.05628   0.04815  -0.0612   0.0246   1.0000
  12.500   1.2900   0.05990   0.05185  -0.0608   0.0224   1.0000
  12.750   1.2888   0.06321   0.05537  -0.0605   0.0207   1.0000
  13.000   1.2871   0.06667   0.05899  -0.0604   0.0194   1.0000
  13.250   1.2853   0.07022   0.06270  -0.0604   0.0184   1.0000
  13.500   1.2833   0.07390   0.06652  -0.0606   0.0176   1.0000
  13.750   1.2805   0.07777   0.07052  -0.0610   0.0169   1.0000
  14.000   1.2773   0.08180   0.07467  -0.0613   0.0163   1.0000
  14.250   1.2767   0.08558   0.07859  -0.0616   0.0158   1.0000
  14.500   1.2773   0.08934   0.08257  -0.0620   0.0154   1.0000
  14.750   1.2766   0.09338   0.08685  -0.0626   0.0149   1.0000
  15.000   1.2741   0.09780   0.09149  -0.0637   0.0145   1.0000
  15.250   1.2701   0.10257   0.09650  -0.0651   0.0141   1.0000
  15.500   1.2644   0.10774   0.10189  -0.0671   0.0137   1.0000
  15.750   1.2576   0.11327   0.10768  -0.0695   0.0134   1.0000
  16.000   1.2496   0.11914   0.11376  -0.0723   0.0131   1.0000
  16.250   1.2406   0.12546   0.12029  -0.0756   0.0129   1.0000
  16.500   1.2305   0.13222   0.12725  -0.0794   0.0128   1.0000
  16.750   1.2190   0.13966   0.13490  -0.0839   0.0127   1.0000
  17.000   1.2052   0.14808   0.14354  -0.0891   0.0128   1.0000
  17.250   1.1884   0.15786   0.15353  -0.0955   0.0129   1.0000
  17.500   1.1649   0.17067   0.16651  -0.1040   0.0136   1.0000
  17.750   1.1377   0.18642   0.18240  -0.1140   0.0144   1.0000
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