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NACA 63-215 AIRFOIL (n63215-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-215 AIRFOIL (n63215-il)
Reynolds number: 100,000
Max Cl/Cd: 48.62 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63215-il-100000.txt
Download as CSV file: xf-n63215-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-215 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5394   0.12898   0.12378  -0.0174   1.0000   0.1579
 -12.250  -0.5709   0.08318   0.07827  -0.0459   1.0000   0.0854
 -12.000  -0.5852   0.07613   0.07119  -0.0483   1.0000   0.0843
 -11.750  -0.6123   0.06833   0.06332  -0.0515   1.0000   0.0827
 -11.500  -0.6516   0.06033   0.05520  -0.0546   1.0000   0.0804
 -11.250  -0.8372   0.06245   0.05625  -0.0522   1.0000   0.0736
 -11.000  -0.8388   0.05782   0.05148  -0.0516   1.0000   0.0730
 -10.750  -0.8428   0.05406   0.04751  -0.0504   1.0000   0.0726
 -10.500  -0.8474   0.05086   0.04400  -0.0487   1.0000   0.0727
 -10.250  -0.8497   0.04811   0.04089  -0.0467   1.0000   0.0732
 -10.000  -0.8488   0.04533   0.03776  -0.0446   1.0000   0.0740
  -9.750  -0.8394   0.04186   0.03413  -0.0435   1.0000   0.0751
  -9.500  -0.8289   0.03943   0.03157  -0.0418   1.0000   0.0762
  -9.250  -0.8196   0.03750   0.02951  -0.0397   1.0000   0.0774
  -9.000  -0.8126   0.03594   0.02784  -0.0370   1.0000   0.0789
  -8.750  -0.8084   0.03471   0.02647  -0.0339   1.0000   0.0809
  -8.500  -0.8047   0.03356   0.02512  -0.0306   1.0000   0.0832
  -8.250  -0.7988   0.03244   0.02374  -0.0277   1.0000   0.0851
  -8.000  -0.7869   0.03072   0.02194  -0.0256   1.0000   0.0873
  -7.750  -0.7746   0.02949   0.02080  -0.0237   1.0000   0.0906
  -7.500  -0.7632   0.02860   0.01982  -0.0217   1.0000   0.0947
  -7.250  -0.7507   0.02780   0.01883  -0.0197   1.0000   0.0986
  -7.000  -0.7220   0.02633   0.01756  -0.0206   0.9966   0.1051
  -6.750  -0.6838   0.02508   0.01633  -0.0232   0.9901   0.1156
  -6.500  -0.6457   0.02385   0.01524  -0.0260   0.9834   0.1300
  -6.250  -0.6140   0.02255   0.01416  -0.0279   0.9751   0.1540
  -6.000  -0.5874   0.02030   0.01267  -0.0299   0.9671   0.2297
  -5.750  -0.5646   0.01874   0.01241  -0.0307   0.9581   0.4455
  -5.500  -0.5316   0.01918   0.01287  -0.0314   0.9492   0.5084
  -5.250  -0.4912   0.01987   0.01350  -0.0331   0.9424   0.5468
  -5.000  -0.4599   0.02053   0.01409  -0.0331   0.9337   0.5736
  -4.750  -0.4189   0.02144   0.01496  -0.0343   0.9275   0.6000
  -4.500  -0.3872   0.02224   0.01572  -0.0339   0.9197   0.6208
  -4.250  -0.3503   0.02308   0.01654  -0.0340   0.9129   0.6383
  -4.000  -0.3158   0.02362   0.01700  -0.0343   0.9063   0.6538
  -3.750  -0.2858   0.02420   0.01754  -0.0334   0.8981   0.6652
  -3.500  -0.2455   0.02465   0.01793  -0.0342   0.8934   0.6769
  -3.250  -0.2270   0.02476   0.01795  -0.0326   0.8829   0.6889
  -3.000  -0.1900   0.02490   0.01801  -0.0334   0.8777   0.6983
  -2.750  -0.1714   0.02495   0.01800  -0.0319   0.8676   0.7071
  -2.500  -0.1383   0.02484   0.01779  -0.0327   0.8619   0.7168
  -2.250  -0.1194   0.02492   0.01784  -0.0312   0.8523   0.7243
  -2.000  -0.0891   0.02478   0.01762  -0.0316   0.8462   0.7334
  -1.750  -0.0694   0.02484   0.01764  -0.0303   0.8372   0.7408
  -1.500  -0.0416   0.02474   0.01748  -0.0302   0.8306   0.7493
  -1.250  -0.0196   0.02475   0.01745  -0.0294   0.8230   0.7570
  -1.000   0.0042   0.02474   0.01741  -0.0287   0.8153   0.7651
  -0.750   0.0353   0.02452   0.01713  -0.0290   0.8108   0.7729
  -0.500   0.0493   0.02477   0.01740  -0.0273   0.8004   0.7808
  -0.250   0.0791   0.02455   0.01713  -0.0275   0.7955   0.7890
   0.000   0.0946   0.02482   0.01742  -0.0259   0.7859   0.7968
   0.250   0.1219   0.02468   0.01725  -0.0258   0.7802   0.8054
   0.500   0.1419   0.02487   0.01745  -0.0246   0.7727   0.8131
   0.750   0.1640   0.02489   0.01747  -0.0240   0.7653   0.8220
   1.000   0.1948   0.02472   0.01730  -0.0237   0.7613   0.8297
   1.250   0.2058   0.02515   0.01778  -0.0221   0.7509   0.8392
   1.500   0.2349   0.02500   0.01762  -0.0218   0.7461   0.8480
   1.750   0.2491   0.02538   0.01806  -0.0202   0.7372   0.8574
   2.000   0.2742   0.02533   0.01802  -0.0197   0.7310   0.8678
   2.250   0.3078   0.02504   0.01775  -0.0196   0.7275   0.8753
   2.500   0.3149   0.02568   0.01847  -0.0174   0.7162   0.8873
   2.750   0.3479   0.02537   0.01818  -0.0175   0.7121   0.8971
   3.000   0.3602   0.02597   0.01888  -0.0160   0.7016   0.9090
   3.250   0.3957   0.02568   0.01863  -0.0167   0.6967   0.9187
   3.500   0.4165   0.02612   0.01916  -0.0164   0.6874   0.9314
   3.750   0.4575   0.02589   0.01900  -0.0183   0.6814   0.9409
   4.000   0.4988   0.02590   0.01909  -0.0208   0.6740   0.9500
   4.250   0.5413   0.02575   0.01905  -0.0234   0.6655   0.9594
   4.500   0.5919   0.02548   0.01888  -0.0272   0.6565   0.9666
   4.750   0.6470   0.02457   0.01805  -0.0309   0.6476   0.9727
   5.000   0.6956   0.02414   0.01774  -0.0345   0.6348   0.9806
   5.250   0.7467   0.02330   0.01701  -0.0379   0.6221   0.9881
   5.500   0.7961   0.02223   0.01600  -0.0408   0.6069   0.9966
   5.750   0.8240   0.02142   0.01521  -0.0402   0.5918   1.0000
   6.000   0.8382   0.02080   0.01459  -0.0374   0.5769   1.0000
   6.250   0.8494   0.02029   0.01408  -0.0342   0.5605   1.0000
   6.500   0.8587   0.01991   0.01371  -0.0309   0.5435   1.0000
   6.750   0.8703   0.01959   0.01342  -0.0280   0.5242   1.0000
   7.000   0.8906   0.01918   0.01301  -0.0263   0.5009   1.0000
   7.250   0.9091   0.01904   0.01292  -0.0248   0.4707   1.0000
   7.500   0.9262   0.01905   0.01290  -0.0231   0.4283   1.0000
   7.750   0.9367   0.01948   0.01303  -0.0205   0.3570   1.0000
   8.000   0.9322   0.02112   0.01391  -0.0166   0.2570   1.0000
   8.250   0.9232   0.02334   0.01548  -0.0127   0.1919   1.0000
   8.500   0.9185   0.02528   0.01700  -0.0093   0.1591   1.0000
   8.750   0.9230   0.02700   0.01850  -0.0069   0.1373   1.0000
   9.000   0.9335   0.02855   0.01990  -0.0053   0.1225   1.0000
   9.250   0.9499   0.03007   0.02126  -0.0043   0.1114   1.0000
   9.500   0.9720   0.03158   0.02259  -0.0038   0.1019   1.0000
   9.750   0.9944   0.03299   0.02411  -0.0033   0.0945   1.0000
  10.000   1.0286   0.03492   0.02586  -0.0042   0.0873   1.0000
  10.250   1.0499   0.03647   0.02761  -0.0037   0.0823   1.0000
  10.500   1.0853   0.03864   0.02969  -0.0051   0.0773   1.0000
  10.750   1.1081   0.04101   0.03230  -0.0049   0.0738   1.0000
  11.000   1.1244   0.04309   0.03463  -0.0040   0.0711   1.0000
  11.250   1.1436   0.04552   0.03726  -0.0035   0.0690   1.0000
  11.500   1.1610   0.04807   0.03994  -0.0031   0.0671   1.0000
  11.750   1.1852   0.05256   0.04450  -0.0041   0.0651   1.0000
  12.000   1.1783   0.05471   0.04702  -0.0011   0.0645   1.0000
  12.250   1.1677   0.05720   0.04984   0.0018   0.0639   1.0000
  12.500   1.1567   0.06019   0.05315   0.0039   0.0636   1.0000
  12.750   1.1428   0.06355   0.05680   0.0056   0.0634   1.0000
  13.000   1.1269   0.06739   0.06091   0.0066   0.0634   1.0000
  13.250   1.1091   0.07168   0.06545   0.0070   0.0636   1.0000
  13.500   1.0897   0.07643   0.07043   0.0068   0.0638   1.0000
  13.750   1.0691   0.08169   0.07590   0.0058   0.0642   1.0000
  14.000   1.0497   0.08745   0.08184   0.0042   0.0646   1.0000
  14.250   1.0335   0.09378   0.08830   0.0023   0.0650   1.0000
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