Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 2421 (naca2421-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 2421 (naca2421-il)
Reynolds number: 100,000
Max Cl/Cd: 41.06 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2421-il-100000-n5.txt
Download as CSV file: xf-naca2421-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2421                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.8418   0.07787   0.07002  -0.0764   1.0000   0.1001
 -16.000  -0.8575   0.07287   0.06490  -0.0784   1.0000   0.1015
 -15.750  -0.8547   0.07052   0.06258  -0.0789   1.0000   0.1029
 -15.500  -0.8645   0.06666   0.05862  -0.0802   1.0000   0.1045
 -15.250  -0.8794   0.06237   0.05419  -0.0814   1.0000   0.1061
 -15.000  -0.8955   0.05822   0.04985  -0.0823   1.0000   0.1078
 -14.750  -0.9124   0.05430   0.04570  -0.0826   1.0000   0.1095
 -14.500  -0.9078   0.05271   0.04416  -0.0820   1.0000   0.1110
 -14.250  -0.9077   0.05084   0.04230  -0.0813   1.0000   0.1127
 -14.000  -0.9114   0.04880   0.04020  -0.0803   1.0000   0.1145
 -13.750  -0.9180   0.04671   0.03800  -0.0789   1.0000   0.1165
 -13.500  -0.9268   0.04466   0.03580  -0.0770   1.0000   0.1186
 -13.250  -0.9287   0.04326   0.03439  -0.0749   1.0000   0.1203
 -13.000  -0.9303   0.04209   0.03324  -0.0725   1.0000   0.1220
 -12.750  -0.9348   0.04091   0.03204  -0.0697   1.0000   0.1240
 -12.500  -0.9420   0.03976   0.03083  -0.0663   1.0000   0.1260
 -12.250  -0.9512   0.03869   0.02965  -0.0623   1.0000   0.1282
 -12.000  -0.9603   0.03777   0.02867  -0.0581   1.0000   0.1301
 -11.750  -0.9681   0.03709   0.02803  -0.0536   1.0000   0.1318
 -11.500  -0.9789   0.03647   0.02741  -0.0485   1.0000   0.1335
 -11.250  -0.9918   0.03592   0.02683  -0.0429   1.0000   0.1353
 -11.000  -0.9709   0.03494   0.02571  -0.0433   0.9948   0.1395
 -10.750  -0.9462   0.03405   0.02481  -0.0443   0.9897   0.1434
 -10.500  -0.9219   0.03322   0.02396  -0.0450   0.9836   0.1477
 -10.250  -0.8936   0.03236   0.02293  -0.0463   0.9787   0.1531
 -10.000  -0.8704   0.03160   0.02225  -0.0466   0.9716   0.1572
  -9.750  -0.8419   0.03085   0.02144  -0.0477   0.9659   0.1629
  -9.500  -0.8154   0.03011   0.02068  -0.0484   0.9595   0.1681
  -9.250  -0.7894   0.02945   0.02003  -0.0489   0.9523   0.1736
  -9.000  -0.7557   0.02874   0.01924  -0.0507   0.9479   0.1805
  -8.750  -0.7353   0.02819   0.01875  -0.0499   0.9387   0.1857
  -8.500  -0.7036   0.02758   0.01806  -0.0512   0.9332   0.1932
  -8.250  -0.6727   0.02699   0.01753  -0.0523   0.9279   0.1998
  -8.000  -0.6506   0.02654   0.01703  -0.0516   0.9187   0.2069
  -7.750  -0.6178   0.02597   0.01649  -0.0530   0.9138   0.2145
  -7.500  -0.5932   0.02554   0.01603  -0.0526   0.9060   0.2225
  -7.250  -0.5673   0.02508   0.01559  -0.0525   0.8982   0.2301
  -7.000  -0.5339   0.02459   0.01505  -0.0537   0.8934   0.2399
  -6.750  -0.5137   0.02424   0.01474  -0.0524   0.8837   0.2475
  -6.500  -0.4849   0.02382   0.01428  -0.0527   0.8767   0.2576
  -6.250  -0.4514   0.02332   0.01382  -0.0538   0.8721   0.2675
  -6.000  -0.4334   0.02309   0.01354  -0.0520   0.8607   0.2771
  -5.750  -0.4030   0.02263   0.01314  -0.0524   0.8543   0.2871
  -5.500  -0.3770   0.02232   0.01276  -0.0521   0.8462   0.2981
  -5.250  -0.3525   0.02197   0.01250  -0.0514   0.8370   0.3075
  -5.000  -0.3194   0.02157   0.01202  -0.0522   0.8312   0.3195
  -4.750  -0.2992   0.02132   0.01186  -0.0507   0.8201   0.3287
  -4.500  -0.2691   0.02098   0.01147  -0.0510   0.8126   0.3405
  -4.250  -0.2435   0.02068   0.01124  -0.0504   0.8037   0.3511
  -4.000  -0.2171   0.02042   0.01095  -0.0500   0.7940   0.3628
  -3.750  -0.1858   0.02005   0.01062  -0.0504   0.7871   0.3752
  -3.500  -0.1642   0.01989   0.01049  -0.0491   0.7753   0.3868
  -3.250  -0.1330   0.01957   0.01016  -0.0494   0.7676   0.4010
  -3.000  -0.1107   0.01942   0.01008  -0.0483   0.7561   0.4136
  -2.750  -0.0813   0.01916   0.00981  -0.0483   0.7473   0.4289
  -2.500  -0.0574   0.01902   0.00971  -0.0474   0.7364   0.4446
  -2.250  -0.0298   0.01881   0.00955  -0.0470   0.7268   0.4614
  -2.000  -0.0049   0.01869   0.00947  -0.0462   0.7164   0.4795
  -1.750   0.0211   0.01855   0.00938  -0.0456   0.7063   0.4994
  -1.500   0.0469   0.01844   0.00931  -0.0449   0.6964   0.5202
  -1.250   0.0718   0.01837   0.00928  -0.0441   0.6860   0.5408
  -1.000   0.0991   0.01828   0.00919  -0.0437   0.6771   0.5611
  -0.750   0.1228   0.01826   0.00922  -0.0427   0.6663   0.5805
  -0.500   0.1520   0.01818   0.00913  -0.0425   0.6582   0.5997
  -0.250   0.1746   0.01821   0.00925  -0.0413   0.6473   0.6177
   0.000   0.2025   0.01818   0.00921  -0.0410   0.6387   0.6366
   0.250   0.2266   0.01823   0.00930  -0.0400   0.6291   0.6556
   0.500   0.2526   0.01825   0.00934  -0.0394   0.6203   0.6748
   0.750   0.2797   0.01830   0.00941  -0.0389   0.6118   0.6930
   1.000   0.3044   0.01839   0.00956  -0.0380   0.6021   0.7111
   1.250   0.3335   0.01843   0.00957  -0.0378   0.5945   0.7299
   1.500   0.3565   0.01858   0.00979  -0.0367   0.5849   0.7487
   1.750   0.3834   0.01869   0.00990  -0.0361   0.5768   0.7678
   2.000   0.4109   0.01886   0.01008  -0.0356   0.5685   0.7854
   2.250   0.4368   0.01904   0.01031  -0.0349   0.5593   0.8033
   2.500   0.4669   0.01919   0.01038  -0.0349   0.5517   0.8213
   2.750   0.4898   0.01941   0.01068  -0.0338   0.5410   0.8401
   3.000   0.5197   0.01959   0.01077  -0.0337   0.5315   0.8578
   3.250   0.5471   0.01986   0.01110  -0.0333   0.5201   0.8747
   3.500   0.5793   0.02009   0.01125  -0.0338   0.5109   0.8911
   3.750   0.6079   0.02039   0.01158  -0.0339   0.5015   0.9077
   4.000   0.6401   0.02066   0.01181  -0.0346   0.4924   0.9223
   4.250   0.6770   0.02096   0.01209  -0.0363   0.4834   0.9329
   4.500   0.7089   0.02124   0.01236  -0.0373   0.4739   0.9456
   4.750   0.7493   0.02153   0.01258  -0.0399   0.4650   0.9541
   5.000   0.7844   0.02183   0.01291  -0.0416   0.4550   0.9642
   5.250   0.8239   0.02209   0.01308  -0.0441   0.4463   0.9725
   5.500   0.8595   0.02240   0.01345  -0.0462   0.4357   0.9814
   5.750   0.8977   0.02267   0.01362  -0.0485   0.4269   0.9897
   6.000   0.9341   0.02301   0.01402  -0.0509   0.4158   0.9975
   6.250   0.9535   0.02322   0.01413  -0.0497   0.4082   1.0000
   6.500   0.9570   0.02347   0.01444  -0.0457   0.4000   1.0000
   6.750   0.9630   0.02368   0.01461  -0.0420   0.3924   1.0000
   7.000   0.9690   0.02394   0.01483  -0.0383   0.3850   1.0000
   7.250   0.9724   0.02424   0.01513  -0.0342   0.3769   1.0000
   7.500   0.9804   0.02450   0.01529  -0.0308   0.3698   1.0000
   7.750   0.9799   0.02485   0.01568  -0.0260   0.3617   1.0000
   8.000   0.9838   0.02518   0.01597  -0.0220   0.3542   1.0000
   8.250   0.9907   0.02559   0.01635  -0.0187   0.3465   1.0000
   8.500   0.9968   0.02609   0.01686  -0.0154   0.3382   1.0000
   8.750   1.0079   0.02656   0.01724  -0.0129   0.3309   1.0000
   9.000   1.0150   0.02722   0.01796  -0.0101   0.3223   1.0000
   9.250   1.0258   0.02781   0.01849  -0.0079   0.3147   1.0000
   9.500   1.0348   0.02855   0.01927  -0.0056   0.3067   1.0000
   9.750   1.0446   0.02929   0.02002  -0.0035   0.2989   1.0000
  10.000   1.0548   0.03009   0.02079  -0.0016   0.2915   1.0000
  10.250   1.0631   0.03101   0.02177   0.0003   0.2836   1.0000
  10.500   1.0738   0.03186   0.02254   0.0020   0.2769   1.0000
  10.750   1.0809   0.03298   0.02376   0.0038   0.2690   1.0000
  11.000   1.0898   0.03399   0.02473   0.0054   0.2623   1.0000
  11.250   1.0971   0.03521   0.02600   0.0069   0.2552   1.0000
  11.500   1.1041   0.03646   0.02726   0.0084   0.2484   1.0000
  11.750   1.1118   0.03772   0.02850   0.0097   0.2422   1.0000
  12.000   1.1168   0.03925   0.03010   0.0110   0.2353   1.0000
  12.250   1.1243   0.04057   0.03136   0.0121   0.2294   1.0000
  12.500   1.1284   0.04231   0.03317   0.0132   0.2230   1.0000
  12.750   1.1329   0.04401   0.03489   0.0142   0.2170   1.0000
  13.000   1.1395   0.04558   0.03642   0.0151   0.2116   1.0000
  13.250   1.1410   0.04770   0.03867   0.0158   0.2056   1.0000
  13.500   1.1457   0.04953   0.04048   0.0165   0.2003   1.0000
  13.750   1.1493   0.05156   0.04255   0.0171   0.1952   1.0000
  14.000   1.1495   0.05402   0.04511   0.0175   0.1897   1.0000
  14.250   1.1542   0.05598   0.04706   0.0179   0.1849   1.0000
  14.500   1.1541   0.05861   0.04978   0.0181   0.1800   1.0000
  14.750   1.1528   0.06143   0.05270   0.0181   0.1750   1.0000
  15.000   1.1574   0.06352   0.05476   0.0182   0.1707   1.0000
  15.250   1.1532   0.06685   0.05823   0.0180   0.1660   1.0000
  15.500   1.1506   0.07003   0.06149   0.0176   0.1614   1.0000
  15.750   1.1555   0.07221   0.06362   0.0175   0.1575   1.0000
  16.000   1.1468   0.07635   0.06794   0.0168   0.1530   1.0000
  16.250   1.1432   0.07983   0.07149   0.0161   0.1488   1.0000
  16.500   1.1488   0.08201   0.07360   0.0158   0.1453   1.0000
  16.750   1.1358   0.08701   0.07881   0.0144   0.1411   1.0000
  17.000   1.1314   0.09076   0.08263   0.0134   0.1372   1.0000
  17.250   1.1386   0.09276   0.08455   0.0131   0.1341   1.0000
  17.500   1.1207   0.09873   0.09075   0.0111   0.1301   1.0000
  17.750   1.1150   0.10287   0.09496   0.0097   0.1265   1.0000
  18.000   1.1245   0.10457   0.09658   0.0093   0.1236   1.0000
  18.250   1.1016   0.11160   0.10385   0.0064   0.1200   1.0000
  18.500   1.0926   0.11645   0.10879   0.0044   0.1166   1.0000
  18.750   1.1044   0.11781   0.11008   0.0040   0.1140   1.0000
  19.000   1.0734   0.12662   0.11912  -0.0001   0.1104   1.0000
<< Back to NACA 2421 (naca2421-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2421 (naca2421-il)