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

NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 MOD B (n64212mb-il)
Reynolds number: 100,000
Max Cl/Cd: 35.07 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212mb-il-100000-n5.txt
Download as CSV file: xf-n64212mb-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD B                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5813   0.09850   0.09302  -0.0228   1.0000   0.0349
 -11.500  -0.5857   0.09230   0.08684  -0.0262   1.0000   0.0346
 -11.250  -0.5969   0.08496   0.07949  -0.0309   1.0000   0.0342
 -11.000  -0.6170   0.07712   0.07159  -0.0365   1.0000   0.0338
 -10.750  -0.6417   0.07016   0.06452  -0.0413   1.0000   0.0335
 -10.500  -0.6650   0.06469   0.05892  -0.0442   1.0000   0.0333
 -10.250  -0.6866   0.06032   0.05440  -0.0451   1.0000   0.0332
 -10.000  -0.7050   0.05687   0.05077  -0.0442   1.0000   0.0330
  -9.750  -0.7166   0.05339   0.04706  -0.0430   1.0000   0.0329
  -9.500  -0.7229   0.04993   0.04331  -0.0417   1.0000   0.0329
  -9.250  -0.7237   0.04670   0.03977  -0.0403   1.0000   0.0329
  -9.000  -0.7204   0.04371   0.03645  -0.0387   1.0000   0.0331
  -8.750  -0.7137   0.04097   0.03338  -0.0372   1.0000   0.0334
  -8.500  -0.7053   0.03846   0.03048  -0.0354   1.0000   0.0341
  -8.250  -0.6956   0.03621   0.02776  -0.0334   1.0000   0.0348
  -8.000  -0.6815   0.03445   0.02592  -0.0319   1.0000   0.0355
  -7.750  -0.6671   0.03299   0.02437  -0.0303   1.0000   0.0361
  -7.500  -0.6526   0.03152   0.02277  -0.0286   1.0000   0.0367
  -7.250  -0.6385   0.03014   0.02126  -0.0266   1.0000   0.0372
  -7.000  -0.6243   0.02887   0.01986  -0.0246   1.0000   0.0378
  -6.750  -0.6101   0.02770   0.01855  -0.0225   1.0000   0.0386
  -6.500  -0.5830   0.02635   0.01705  -0.0227   0.9959   0.0396
  -6.250  -0.5494   0.02507   0.01559  -0.0241   0.9894   0.0413
  -6.000  -0.5157   0.02397   0.01457  -0.0258   0.9834   0.0436
  -5.750  -0.4831   0.02301   0.01357  -0.0271   0.9763   0.0464
  -5.500  -0.4494   0.02202   0.01252  -0.0285   0.9704   0.0488
  -5.250  -0.4177   0.02111   0.01169  -0.0299   0.9634   0.0521
  -5.000  -0.3838   0.02036   0.01089  -0.0314   0.9575   0.0573
  -4.750  -0.3536   0.01960   0.01017  -0.0323   0.9498   0.0629
  -4.500  -0.3209   0.01888   0.00945  -0.0336   0.9437   0.0720
  -4.250  -0.2926   0.01820   0.00882  -0.0341   0.9352   0.0857
  -4.000  -0.2611   0.01726   0.00814  -0.0354   0.9294   0.1261
  -3.750  -0.2421   0.01561   0.00747  -0.0351   0.9196   0.3064
  -3.500  -0.2164   0.01484   0.00758  -0.0348   0.9135   0.5118
  -3.250  -0.1911   0.01483   0.00769  -0.0339   0.9048   0.5691
  -3.000  -0.1626   0.01498   0.00795  -0.0332   0.8980   0.6253
  -2.750  -0.1397   0.01535   0.00845  -0.0308   0.8874   0.6736
  -2.500  -0.1125   0.01552   0.00859  -0.0294   0.8759   0.7008
  -2.250  -0.0836   0.01541   0.00837  -0.0286   0.8621   0.7094
  -2.000  -0.0570   0.01525   0.00809  -0.0277   0.8463   0.7186
  -1.750  -0.0314   0.01515   0.00790  -0.0266   0.8313   0.7259
  -1.500  -0.0047   0.01501   0.00765  -0.0260   0.8175   0.7345
  -1.250   0.0217   0.01492   0.00751  -0.0251   0.8049   0.7403
  -1.000   0.0487   0.01480   0.00729  -0.0244   0.7920   0.7479
  -0.750   0.0747   0.01469   0.00712  -0.0236   0.7773   0.7551
  -0.500   0.1004   0.01460   0.00699  -0.0227   0.7617   0.7623
  -0.250   0.1268   0.01450   0.00682  -0.0221   0.7455   0.7702
   0.000   0.1521   0.01442   0.00670  -0.0210   0.7274   0.7771
   0.250   0.1781   0.01434   0.00653  -0.0202   0.7055   0.7864
   0.500   0.2023   0.01427   0.00641  -0.0189   0.6777   0.7934
   0.750   0.2274   0.01423   0.00623  -0.0179   0.6414   0.8025
   1.000   0.2507   0.01425   0.00608  -0.0163   0.5854   0.8100
   1.250   0.2689   0.01474   0.00579  -0.0141   0.4182   0.8200
   1.500   0.2863   0.01554   0.00599  -0.0122   0.3307   0.8287
   1.750   0.3087   0.01597   0.00620  -0.0113   0.3009   0.8390
   2.000   0.3315   0.01629   0.00640  -0.0103   0.2822   0.8486
   2.250   0.3545   0.01658   0.00659  -0.0094   0.2690   0.8589
   2.500   0.3782   0.01683   0.00679  -0.0086   0.2586   0.8708
   2.750   0.4013   0.01709   0.00699  -0.0075   0.2511   0.8819
   3.000   0.4256   0.01731   0.00720  -0.0067   0.2440   0.8939
   3.250   0.4499   0.01760   0.00741  -0.0060   0.2382   0.9072
   3.500   0.4762   0.01785   0.00765  -0.0057   0.2324   0.9212
   3.750   0.5046   0.01813   0.00791  -0.0059   0.2267   0.9356
   4.000   0.5362   0.01850   0.00820  -0.0067   0.2218   0.9500
   4.250   0.5714   0.01890   0.00858  -0.0084   0.2175   0.9643
   4.500   0.6086   0.01931   0.00901  -0.0105   0.2132   0.9807
   4.750   0.6410   0.01974   0.00942  -0.0119   0.2093   1.0000
   5.000   0.6651   0.02021   0.00982  -0.0116   0.2061   1.0000
   5.250   0.6906   0.02078   0.01029  -0.0116   0.2030   1.0000
   5.500   0.7168   0.02124   0.01084  -0.0116   0.1998   1.0000
   5.750   0.7432   0.02178   0.01143  -0.0116   0.1968   1.0000
   6.000   0.7698   0.02235   0.01203  -0.0117   0.1940   1.0000
   6.250   0.7963   0.02294   0.01263  -0.0117   0.1913   1.0000
   6.500   0.8228   0.02358   0.01324  -0.0118   0.1886   1.0000
   6.750   0.8492   0.02431   0.01397  -0.0119   0.1860   1.0000
   7.000   0.8748   0.02497   0.01480  -0.0118   0.1832   1.0000
   7.250   0.9004   0.02571   0.01568  -0.0117   0.1806   1.0000
   7.500   0.9256   0.02642   0.01651  -0.0116   0.1777   1.0000
   7.750   0.9507   0.02711   0.01725  -0.0115   0.1748   1.0000
   8.000   0.9762   0.02784   0.01799  -0.0114   0.1722   1.0000
   8.250   1.0010   0.02874   0.01895  -0.0113   0.1697   1.0000
   8.500   1.0229   0.02958   0.02008  -0.0108   0.1662   1.0000
   8.750   1.0452   0.03035   0.02104  -0.0104   0.1623   1.0000
   9.000   1.0682   0.03097   0.02174  -0.0100   0.1588   1.0000
   9.250   1.0925   0.03155   0.02227  -0.0099   0.1558   1.0000
   9.500   1.1115   0.03251   0.02354  -0.0091   0.1519   1.0000
   9.750   1.1303   0.03335   0.02463  -0.0083   0.1474   1.0000
  10.000   1.1510   0.03382   0.02517  -0.0077   0.1435   1.0000
  10.250   1.1742   0.03414   0.02541  -0.0074   0.1403   1.0000
  10.500   1.1866   0.03531   0.02703  -0.0060   0.1353   1.0000
  10.750   1.2033   0.03589   0.02777  -0.0050   0.1308   1.0000
  11.000   1.2230   0.03602   0.02787  -0.0042   0.1273   1.0000
  11.250   1.2333   0.03724   0.02945  -0.0027   0.1224   1.0000
  11.500   1.2457   0.03794   0.03033  -0.0013   0.1178   1.0000
  11.750   1.2609   0.03805   0.03042  -0.0001   0.1143   1.0000
  12.000   1.2635   0.03958   0.03230   0.0020   0.1092   1.0000
  12.250   1.2697   0.04034   0.03319   0.0039   0.1050   1.0000
  12.500   1.2762   0.04106   0.03395   0.0055   0.1015   1.0000
  12.750   1.2742   0.04305   0.03624   0.0071   0.0966   1.0000
  13.000   1.2775   0.04425   0.03750   0.0083   0.0928   1.0000
  13.250   1.2751   0.04641   0.03982   0.0091   0.0892   1.0000
  13.500   1.2688   0.04915   0.04276   0.0096   0.0854   1.0000
  13.750   1.2656   0.05155   0.04521   0.0096   0.0824   1.0000
  14.000   1.2546   0.05525   0.04905   0.0090   0.0799   1.0000
  14.250   1.2334   0.06071   0.05476   0.0072   0.0778   1.0000
  14.500   1.2033   0.06807   0.06236   0.0036   0.0767   1.0000
  14.750   1.1073   0.08920   0.08385  -0.0097   0.0796   1.0000
<< Back to NACA 64(1)-212 MOD B (n64212mb-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(1)-212 MOD B (n64212mb-il)