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NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(2)-415 (naca652415-il)
Reynolds number: 100,000
Max Cl/Cd: 46.67 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca652415-il-100000.txt
Download as CSV file: xf-naca652415-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4552   0.10131   0.09661  -0.0570   1.0000   0.1604
 -10.250  -0.4085   0.09876   0.09396  -0.0514   1.0000   0.1648
 -10.000  -0.4145   0.09699   0.09229  -0.0493   1.0000   0.1719
  -9.750  -0.4730   0.09522   0.09075  -0.0480   1.0000   0.1751
  -9.500  -0.5355   0.09322   0.08896  -0.0462   1.0000   0.1757
  -9.250  -0.4696   0.09255   0.08817  -0.0395   1.0000   0.1850
  -9.000  -0.5078   0.09071   0.08648  -0.0372   1.0000   0.1885
  -8.750  -0.5617   0.08789   0.08383  -0.0362   1.0000   0.1899
  -8.500  -0.5455   0.08675   0.08269  -0.0318   0.9999   0.1979
  -8.250  -0.6319   0.07788   0.07364  -0.0475   0.9816   0.2071
  -7.250  -0.6194   0.04488   0.03746  -0.0555   0.9519   0.0853
  -7.000  -0.5970   0.04139   0.03370  -0.0559   0.9465   0.0831
  -6.750  -0.5656   0.03831   0.03017  -0.0574   0.9425   0.0810
  -6.500  -0.5434   0.03631   0.02780  -0.0569   0.9369   0.0807
  -6.250  -0.5187   0.03480   0.02597  -0.0568   0.9315   0.0827
  -6.000  -0.4844   0.03320   0.02404  -0.0581   0.9277   0.0841
  -5.750  -0.4521   0.03189   0.02248  -0.0590   0.9237   0.0852
  -5.500  -0.4323   0.03095   0.02137  -0.0576   0.9173   0.0868
  -5.250  -0.4005   0.02951   0.02009  -0.0587   0.9135   0.0917
  -5.000  -0.3638   0.02862   0.01917  -0.0604   0.9105   0.0974
  -4.750  -0.3499   0.02823   0.01871  -0.0581   0.9043   0.1007
  -4.500  -0.3280   0.02734   0.01801  -0.0576   0.8991   0.1079
  -4.250  -0.2965   0.02652   0.01730  -0.0587   0.8954   0.1230
  -3.750  -0.2807   0.02320   0.01652  -0.0542   0.8848   0.5403
  -3.500  -0.2614   0.02459   0.01806  -0.0499   0.8802   0.6695
  -3.250  -0.2434   0.02571   0.01914  -0.0463   0.8755   0.7028
  -3.000  -0.2377   0.02656   0.01996  -0.0415   0.8693   0.7232
  -2.750  -0.2222   0.02760   0.02096  -0.0374   0.8651   0.7491
  -2.500  -0.2096   0.02932   0.02273  -0.0299   0.8618   0.7838
  -2.250  -0.2218   0.03019   0.02363  -0.0213   0.8547   0.8053
  -2.000  -0.2143   0.03109   0.02450  -0.0151   0.8504   0.8310
  -1.750  -0.1885   0.03131   0.02459  -0.0144   0.8473   0.8445
  -1.500  -0.1715   0.03146   0.02463  -0.0130   0.8430   0.8523
  -1.250  -0.1665   0.03142   0.02452  -0.0103   0.8372   0.8609
  -1.000  -0.1427   0.03150   0.02450  -0.0103   0.8336   0.8673
  -0.750  -0.1115   0.03150   0.02436  -0.0120   0.8306   0.8742
  -0.500  -0.1037   0.03166   0.02449  -0.0095   0.8254   0.8806
  -0.250  -0.0922   0.03175   0.02451  -0.0081   0.8207   0.8887
   0.000  -0.0661   0.03190   0.02460  -0.0086   0.8172   0.8943
   0.250  -0.0293   0.03205   0.02466  -0.0107   0.8142   0.9001
   0.500  -0.0280   0.03230   0.02489  -0.0079   0.8087   0.9084
   0.750  -0.0121   0.03254   0.02510  -0.0072   0.8044   0.9165
   1.000   0.0197   0.03275   0.02525  -0.0086   0.8005   0.9230
   1.250   0.0618   0.03303   0.02549  -0.0116   0.7976   0.9286
   1.500   0.0618   0.03350   0.02596  -0.0091   0.7915   0.9390
   1.750   0.0888   0.03383   0.02628  -0.0103   0.7867   0.9477
   2.000   0.1353   0.03423   0.02666  -0.0143   0.7832   0.9531
   2.250   0.1604   0.03484   0.02729  -0.0158   0.7775   0.9618
   2.500   0.1976   0.03547   0.02794  -0.0193   0.7718   0.9689
   2.750   0.2503   0.03587   0.02836  -0.0244   0.7677   0.9741
   3.000   0.2866   0.03668   0.02922  -0.0282   0.7612   0.9809
   3.250   0.3305   0.03729   0.02988  -0.0327   0.7549   0.9869
   3.500   0.3896   0.03754   0.03019  -0.0385   0.7511   0.9914
   3.750   0.3863   0.03835   0.03104  -0.0364   0.7415   1.0000
   4.000   0.4073   0.03831   0.03102  -0.0358   0.7361   1.0000
   4.250   0.4019   0.03898   0.03169  -0.0328   0.7264   1.0000
   4.500   0.4417   0.03910   0.03186  -0.0351   0.7206   1.0000
   4.750   0.4557   0.03995   0.03276  -0.0349   0.7105   1.0000
   5.000   0.4996   0.03996   0.03285  -0.0375   0.7047   1.0000
   5.250   0.5160   0.04082   0.03376  -0.0375   0.6936   1.0000
   5.500   0.5671   0.04037   0.03344  -0.0402   0.6883   1.0000
   5.750   0.5841   0.04110   0.03424  -0.0399   0.6758   1.0000
   6.000   0.6363   0.04026   0.03355  -0.0422   0.6701   1.0000
   6.250   0.6640   0.04025   0.03366  -0.0424   0.6582   1.0000
   6.500   0.6910   0.04022   0.03376  -0.0423   0.6457   1.0000
   6.750   0.8632   0.02704   0.02102  -0.0481   0.6323   1.0000
   7.000   0.9453   0.02210   0.01624  -0.0511   0.6087   1.0000
   7.250   0.9651   0.02100   0.01523  -0.0485   0.5777   1.0000
   7.500   0.9673   0.02074   0.01503  -0.0439   0.5354   1.0000
   7.750   0.9632   0.02064   0.01416  -0.0375   0.3921   1.0000
   8.000   0.9359   0.02327   0.01571  -0.0308   0.2584   1.0000
   8.250   0.9117   0.02653   0.01807  -0.0259   0.1635   1.0000
   8.500   0.9039   0.02910   0.02017  -0.0227   0.1250   1.0000
   8.750   0.9074   0.03103   0.02191  -0.0205   0.1063   1.0000
   9.000   0.9160   0.03274   0.02345  -0.0188   0.0959   1.0000
   9.250   0.9322   0.03404   0.02474  -0.0177   0.0871   1.0000
   9.500   0.9561   0.03535   0.02595  -0.0170   0.0801   1.0000
   9.750   0.9885   0.03654   0.02711  -0.0171   0.0750   1.0000
  10.000   1.0409   0.03836   0.02882  -0.0192   0.0697   1.0000
  10.250   1.0738   0.04003   0.03070  -0.0197   0.0661   1.0000
  10.500   1.1180   0.04241   0.03323  -0.0217   0.0637   1.0000
  10.750   1.1577   0.04533   0.03636  -0.0234   0.0624   1.0000
  11.000   1.1919   0.04883   0.04007  -0.0251   0.0611   1.0000
  11.250   1.2204   0.05397   0.04547  -0.0265   0.0598   1.0000
  11.500   1.2198   0.05618   0.04806  -0.0235   0.0595   1.0000
  11.750   1.2260   0.05976   0.05195  -0.0218   0.0596   1.0000
  12.000   1.2353   0.06373   0.05621  -0.0206   0.0601   1.0000
  12.250   1.2238   0.06535   0.05815  -0.0166   0.0607   1.0000
  12.500   1.1880   0.06766   0.06098  -0.0113   0.0621   1.0000
  12.750   1.1498   0.07207   0.06588  -0.0078   0.0639   1.0000
  13.000   1.1219   0.07705   0.07120  -0.0062   0.0654   1.0000
  13.250   1.0969   0.08231   0.07672  -0.0056   0.0668   1.0000
  13.500   1.0721   0.08793   0.08255  -0.0059   0.0680   1.0000
  13.750   1.0536   0.09383   0.08861  -0.0069   0.0693   1.0000
  14.000   0.8621   0.09851   0.09400  -0.0047   0.0686   1.0000
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