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BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BE50 (smoothed) (be50sm-il)
Reynolds number: 200,000
Max Cl/Cd: 81.22 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-be50sm-il-200000.txt
Download as CSV file: xf-be50sm-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BE50 (smoothed)                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3577   0.09125   0.08784  -0.0239   1.0000   0.0391
  -7.250  -0.3624   0.08937   0.08604  -0.0259   1.0000   0.0399
  -7.000  -0.3599   0.08687   0.08361  -0.0304   1.0000   0.0404
  -6.750  -0.3545   0.08384   0.08061  -0.0341   1.0000   0.0407
  -6.500  -0.3473   0.08050   0.07729  -0.0372   1.0000   0.0408
  -6.250  -0.3499   0.07512   0.07197  -0.0371   1.0000   0.0415
  -6.000  -0.3494   0.07247   0.06936  -0.0337   1.0000   0.0423
  -5.750  -0.3452   0.07017   0.06709  -0.0320   1.0000   0.0432
  -5.500  -0.3384   0.06763   0.06457  -0.0320   1.0000   0.0444
  -5.250  -0.3284   0.06468   0.06160  -0.0336   1.0000   0.0461
  -5.000  -0.3129   0.06106   0.05796  -0.0372   1.0000   0.0487
  -4.750  -0.2624   0.05158   0.04807  -0.0552   1.0000   0.0539
  -4.500  -0.2599   0.05029   0.04695  -0.0513   1.0000   0.0556
  -4.250  -0.2334   0.04777   0.04440  -0.0536   0.9981   0.0594
  -4.000  -0.1706   0.03980   0.03588  -0.0675   0.9954   0.0682
  -3.750  -0.1341   0.03701   0.03307  -0.0711   0.9921   0.0718
  -3.500  -0.0838   0.03226   0.02779  -0.0784   0.9888   0.0826
  -3.250  -0.0217   0.02142   0.01520  -0.0841   0.9907   0.0404
  -3.000   0.0200   0.01890   0.01233  -0.0876   0.9882   0.0454
  -2.750   0.0640   0.01721   0.01028  -0.0906   0.9855   0.0485
  -2.500   0.1109   0.01580   0.00861  -0.0942   0.9817   0.0556
  -2.250   0.1559   0.01478   0.00752  -0.0973   0.9744   0.0637
  -2.000   0.2040   0.01386   0.00658  -0.1012   0.9702   0.0785
  -1.750   0.2429   0.01304   0.00586  -0.1035   0.9629   0.1007
  -1.500   0.2875   0.01226   0.00530  -0.1069   0.9583   0.1569
  -1.250   0.3298   0.01133   0.00500  -0.1101   0.9530   0.3139
  -1.000   0.3670   0.01064   0.00490  -0.1120   0.9454   0.5114
  -0.750   0.3982   0.00977   0.00471  -0.1121   0.9373   0.7090
  -0.500   0.4290   0.00912   0.00432  -0.1115   0.9282   1.0000
  -0.250   0.4598   0.00901   0.00408  -0.1116   0.9158   1.0000
   0.000   0.4896   0.00892   0.00387  -0.1114   0.9028   1.0000
   0.250   0.5184   0.00883   0.00368  -0.1110   0.8886   1.0000
   0.500   0.5465   0.00877   0.00351  -0.1105   0.8734   1.0000
   0.750   0.5741   0.00872   0.00336  -0.1098   0.8571   1.0000
   1.000   0.6006   0.00873   0.00328  -0.1090   0.8372   1.0000
   1.250   0.6274   0.00875   0.00319  -0.1082   0.8171   1.0000
   1.500   0.6539   0.00881   0.00314  -0.1074   0.7947   1.0000
   1.750   0.6804   0.00890   0.00310  -0.1066   0.7712   1.0000
   2.000   0.7065   0.00903   0.00312  -0.1058   0.7449   1.0000
   2.250   0.7325   0.00920   0.00315  -0.1051   0.7166   1.0000
   2.500   0.7583   0.00941   0.00321  -0.1043   0.6857   1.0000
   2.750   0.7838   0.00965   0.00330  -0.1035   0.6518   1.0000
   3.000   0.8089   0.00996   0.00343  -0.1027   0.6159   1.0000
   3.250   0.8339   0.01030   0.00359  -0.1019   0.5770   1.0000
   3.500   0.8586   0.01068   0.00379  -0.1011   0.5382   1.0000
   3.750   0.8832   0.01112   0.00402  -0.1004   0.5023   1.0000
   4.000   0.9080   0.01155   0.00432  -0.0998   0.4709   1.0000
   4.250   0.9329   0.01201   0.00463  -0.0992   0.4445   1.0000
   4.500   0.9581   0.01244   0.00497  -0.0987   0.4215   1.0000
   4.750   0.9832   0.01292   0.00533  -0.0982   0.4025   1.0000
   5.000   1.0086   0.01335   0.00573  -0.0978   0.3848   1.0000
   5.250   1.0339   0.01379   0.00617  -0.0973   0.3686   1.0000
   5.500   1.0592   0.01424   0.00660  -0.0968   0.3536   1.0000
   5.750   1.0844   0.01469   0.00705  -0.0964   0.3393   1.0000
   6.000   1.1094   0.01513   0.00751  -0.0959   0.3255   1.0000
   6.250   1.1342   0.01556   0.00800  -0.0954   0.3111   1.0000
   6.500   1.1581   0.01588   0.00833  -0.0947   0.2915   1.0000
   6.750   1.1817   0.01620   0.00867  -0.0941   0.2706   1.0000
   7.000   1.2057   0.01654   0.00906  -0.0935   0.2509   1.0000
   7.250   1.2290   0.01694   0.00949  -0.0928   0.2303   1.0000
   7.500   1.2524   0.01735   0.00994  -0.0921   0.2061   1.0000
   7.750   1.2747   0.01791   0.01047  -0.0914   0.1708   1.0000
   8.000   1.2856   0.02011   0.01190  -0.0893   0.0706   1.0000
   8.250   1.2983   0.02213   0.01378  -0.0871   0.0459   1.0000
   8.500   1.3101   0.02401   0.01570  -0.0847   0.0389   1.0000
   8.750   1.3261   0.02531   0.01716  -0.0828   0.0352   1.0000
   9.000   1.3389   0.02686   0.01880  -0.0808   0.0315   1.0000
   9.250   1.3456   0.02930   0.02129  -0.0779   0.0293   1.0000
   9.500   1.3600   0.03086   0.02301  -0.0758   0.0280   1.0000
   9.750   1.3735   0.03266   0.02496  -0.0737   0.0265   1.0000
  10.000   1.3862   0.03437   0.02680  -0.0718   0.0248   1.0000
  10.250   1.3969   0.03617   0.02866  -0.0698   0.0231   1.0000
  10.500   1.4078   0.03942   0.03202  -0.0680   0.0218   1.0000
  10.750   1.4183   0.04400   0.03689  -0.0662   0.0212   1.0000
  11.000   1.4235   0.04632   0.03951  -0.0636   0.0209   1.0000
  11.250   1.4236   0.04897   0.04248  -0.0604   0.0208   1.0000
  11.500   1.4200   0.05194   0.04575  -0.0573   0.0207   1.0000
  11.750   1.4126   0.05522   0.04932  -0.0543   0.0206   1.0000
  12.000   1.4020   0.05882   0.05319  -0.0518   0.0207   1.0000
  12.250   1.3888   0.06285   0.05749  -0.0498   0.0207   1.0000
  12.500   1.3732   0.06732   0.06222  -0.0486   0.0208   1.0000
  12.750   1.3557   0.07241   0.06754  -0.0482   0.0209   1.0000
  13.000   1.3376   0.07892   0.07429  -0.0484   0.0213   1.0000
  13.250   1.3242   0.08336   0.07892  -0.0494   0.0214   1.0000
  13.500   1.3096   0.08835   0.08410  -0.0514   0.0215   1.0000
  13.750   1.2938   0.09398   0.08992  -0.0542   0.0216   1.0000
  14.000   1.2776   0.10016   0.09629  -0.0578   0.0217   1.0000
  14.250   1.2601   0.10714   0.10346  -0.0625   0.0219   1.0000
  14.500   1.2397   0.11557   0.11210  -0.0687   0.0222   1.0000
  14.750   1.2120   0.12706   0.12382  -0.0774   0.0227   1.0000
  15.000   1.1179   0.16410   0.16112  -0.1034   0.0261   1.0000
  15.250   1.0933   0.18261   0.17954  -0.1125   0.0324   1.0000
  15.500   1.1065   0.18103   0.17802  -0.1109   0.0307   1.0000
  16.000   0.8302   0.18196   0.17904  -0.0841   0.0612   1.0000
  16.250   0.8150   0.18703   0.18409  -0.0885   0.0602   1.0000
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