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

NACA 66(3)-218 (naca663218-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(3)-218 (naca663218-il)
Reynolds number: 200,000
Max Cl/Cd: 41.47 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca663218-il-200000-n5.txt
Download as CSV file: xf-naca663218-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(3)-218                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.6453   0.09591   0.09157  -0.0806   1.0000   0.0226
 -16.250  -0.6729   0.08742   0.08292  -0.0856   1.0000   0.0225
 -15.750  -0.7194   0.07195   0.06693  -0.0959   0.9640   0.0225
 -15.500  -0.7358   0.06598   0.06064  -0.0996   0.9546   0.0225
 -15.250  -0.7483   0.06106   0.05542  -0.1020   0.9460   0.0225
 -15.000  -0.7614   0.05673   0.05075  -0.1032   0.9367   0.0226
 -14.750  -0.7633   0.05382   0.04766  -0.1036   0.9283   0.0228
 -14.500  -0.7611   0.05150   0.04520  -0.1037   0.9205   0.0231
 -14.250  -0.7593   0.04942   0.04298  -0.1033   0.9130   0.0233
 -14.000  -0.7565   0.04759   0.04102  -0.1027   0.9059   0.0236
 -13.750  -0.7547   0.04555   0.03877  -0.1018   0.8998   0.0238
 -13.500  -0.7514   0.04373   0.03678  -0.1006   0.8933   0.0240
 -13.250  -0.7456   0.04206   0.03492  -0.0996   0.8878   0.0243
 -13.000  -0.7387   0.04042   0.03309  -0.0984   0.8828   0.0247
 -12.750  -0.7288   0.03884   0.03133  -0.0974   0.8777   0.0249
 -12.500  -0.7166   0.03737   0.02966  -0.0965   0.8734   0.0251
 -12.250  -0.7025   0.03601   0.02809  -0.0956   0.8697   0.0256
 -12.000  -0.6863   0.03477   0.02666  -0.0949   0.8661   0.0260
 -11.750  -0.6688   0.03365   0.02538  -0.0943   0.8623   0.0264
 -11.500  -0.6498   0.03263   0.02420  -0.0938   0.8587   0.0268
 -11.250  -0.6288   0.03164   0.02313  -0.0934   0.8556   0.0273
 -11.000  -0.6097   0.03079   0.02225  -0.0929   0.8527   0.0278
 -10.750  -0.5913   0.03002   0.02142  -0.0923   0.8499   0.0283
 -10.500  -0.5735   0.02927   0.02065  -0.0917   0.8466   0.0293
 -10.250  -0.5553   0.02856   0.01987  -0.0910   0.8434   0.0303
 -10.000  -0.5367   0.02785   0.01908  -0.0903   0.8404   0.0311
  -9.750  -0.5185   0.02717   0.01830  -0.0895   0.8376   0.0318
  -9.500  -0.5026   0.02637   0.01748  -0.0884   0.8350   0.0327
  -9.250  -0.4870   0.02566   0.01674  -0.0873   0.8324   0.0335
  -9.000  -0.4716   0.02499   0.01607  -0.0863   0.8293   0.0346
  -8.750  -0.4561   0.02436   0.01540  -0.0852   0.8264   0.0357
  -8.500  -0.4407   0.02375   0.01472  -0.0840   0.8237   0.0369
  -8.250  -0.4262   0.02311   0.01406  -0.0827   0.8212   0.0389
  -8.000  -0.4114   0.02250   0.01343  -0.0814   0.8190   0.0407
  -7.750  -0.3956   0.02197   0.01283  -0.0801   0.8170   0.0433
  -7.500  -0.3805   0.02142   0.01224  -0.0788   0.8150   0.0454
  -7.250  -0.3656   0.02090   0.01174  -0.0775   0.8125   0.0487
  -7.000  -0.3501   0.02042   0.01125  -0.0761   0.8100   0.0534
  -6.750  -0.3350   0.01993   0.01078  -0.0747   0.8077   0.0604
  -6.500  -0.3216   0.01937   0.01028  -0.0730   0.8055   0.0736
  -6.250  -0.3106   0.01873   0.00978  -0.0710   0.8034   0.0991
  -6.000  -0.3062   0.01784   0.00919  -0.0680   0.8014   0.1569
  -5.750  -0.3048   0.01693   0.00859  -0.0644   0.7993   0.2238
  -5.500  -0.3094   0.01615   0.00813  -0.0596   0.7964   0.2894
  -5.250  -0.3209   0.01558   0.00788  -0.0533   0.7931   0.3503
  -5.000  -0.3310   0.01493   0.00761  -0.0470   0.7901   0.4281
  -4.750  -0.3346   0.01434   0.00756  -0.0414   0.7878   0.5251
  -4.500  -0.3077   0.01491   0.00864  -0.0402   0.7866   0.6323
  -4.250  -0.2908   0.01509   0.00876  -0.0381   0.7850   0.6640
  -4.000  -0.2700   0.01557   0.00920  -0.0365   0.7838   0.6909
  -3.750  -0.2386   0.01657   0.01020  -0.0361   0.7829   0.7107
  -3.500  -0.2149   0.01694   0.01049  -0.0351   0.7819   0.7223
  -3.250  -0.1800   0.01761   0.01113  -0.0358   0.7810   0.7269
  -3.000  -0.1628   0.01783   0.01132  -0.0342   0.7785   0.7338
  -2.750  -0.1446   0.01791   0.01135  -0.0328   0.7761   0.7389
  -2.500  -0.1177   0.01815   0.01156  -0.0327   0.7744   0.7409
  -2.250  -0.0921   0.01833   0.01171  -0.0324   0.7729   0.7433
  -2.000  -0.0685   0.01842   0.01176  -0.0319   0.7714   0.7464
  -1.750  -0.0498   0.01832   0.01161  -0.0308   0.7698   0.7512
  -1.500  -0.0302   0.01816   0.01138  -0.0299   0.7685   0.7552
  -1.250  -0.0027   0.01823   0.01143  -0.0300   0.7674   0.7566
  -1.000   0.0251   0.01826   0.01142  -0.0302   0.7664   0.7580
  -0.750   0.0525   0.01827   0.01140  -0.0304   0.7654   0.7595
  -0.500   0.0793   0.01828   0.01139  -0.0306   0.7646   0.7613
  -0.250   0.0845   0.01871   0.01187  -0.0272   0.7602   0.7645
   0.000   0.0984   0.01881   0.01197  -0.0253   0.7569   0.7674
   0.250   0.1177   0.01874   0.01186  -0.0244   0.7545   0.7704
   0.500   0.1418   0.01863   0.01173  -0.0243   0.7527   0.7722
   0.750   0.1690   0.01860   0.01170  -0.0245   0.7512   0.7730
   1.000   0.1972   0.01857   0.01168  -0.0248   0.7501   0.7740
   1.250   0.2266   0.01853   0.01165  -0.0253   0.7490   0.7751
   1.500   0.2568   0.01848   0.01160  -0.0260   0.7480   0.7762
   2.000   0.2690   0.01927   0.01251  -0.0194   0.7368   0.7800
   2.250   0.2986   0.01914   0.01239  -0.0200   0.7351   0.7813
   2.500   0.3302   0.01897   0.01223  -0.0209   0.7337   0.7826
   2.750   0.3630   0.01878   0.01207  -0.0221   0.7325   0.7839
   3.000   0.3971   0.01857   0.01188  -0.0235   0.7314   0.7853
   3.500   0.4104   0.01920   0.01262  -0.0171   0.7186   0.7902
   3.750   0.4476   0.01885   0.01232  -0.0188   0.7171   0.7910
   4.250   0.4707   0.01904   0.01265  -0.0133   0.7042   0.7940
   4.500   0.5124   0.01849   0.01217  -0.0156   0.7018   0.7949
   4.750   0.5617   0.01774   0.01149  -0.0191   0.6995   0.7957
   5.000   0.5420   0.01836   0.01218  -0.0111   0.6879   0.7987
   5.250   0.5912   0.01742   0.01130  -0.0144   0.6840   0.7996
   5.500   0.5853   0.01774   0.01168  -0.0088   0.6704   0.8026
   5.750   0.6038   0.01716   0.01111  -0.0068   0.6509   0.8049
   6.000   0.5836   0.01859   0.01260  -0.0001   0.6263   0.8082
   6.250   0.6544   0.01578   0.00935  -0.0045   0.5372   0.8084
   6.500   0.6618   0.01624   0.00936  -0.0009   0.4659   0.8105
   6.750   0.6568   0.01725   0.01007   0.0040   0.4074   0.8132
   7.000   0.6509   0.01843   0.01096   0.0086   0.3502   0.8161
   7.250   0.6473   0.01965   0.01190   0.0125   0.2962   0.8192
   7.500   0.6457   0.02092   0.01287   0.0159   0.2410   0.8222
   7.750   0.6468   0.02218   0.01382   0.0188   0.1852   0.8250
   8.000   0.6491   0.02340   0.01476   0.0215   0.1313   0.8272
   8.250   0.6541   0.02458   0.01570   0.0239   0.0891   0.8297
   8.500   0.6637   0.02555   0.01654   0.0256   0.0667   0.8324
   8.750   0.6762   0.02640   0.01735   0.0270   0.0549   0.8352
   9.000   0.6893   0.02724   0.01817   0.0282   0.0474   0.8382
   9.250   0.7032   0.02808   0.01901   0.0292   0.0426   0.8413
   9.500   0.7166   0.02888   0.01988   0.0304   0.0398   0.8438
   9.750   0.7293   0.02973   0.02079   0.0317   0.0372   0.8467
  10.000   0.7409   0.03070   0.02179   0.0330   0.0347   0.8501
  10.250   0.7543   0.03159   0.02276   0.0340   0.0330   0.8538
  10.500   0.7668   0.03258   0.02378   0.0350   0.0311   0.8576
  10.750   0.7770   0.03366   0.02491   0.0363   0.0302   0.8610
  11.000   0.7880   0.03470   0.02603   0.0375   0.0292   0.8645
  11.250   0.7996   0.03576   0.02719   0.0386   0.0282   0.8684
  11.500   0.8118   0.03686   0.02835   0.0396   0.0272   0.8726
  11.750   0.8238   0.03798   0.02953   0.0404   0.0265   0.8767
  12.000   0.8347   0.03914   0.03075   0.0415   0.0259   0.8807
  12.250   0.8458   0.04040   0.03202   0.0424   0.0253   0.8853
  12.500   0.8594   0.04155   0.03326   0.0431   0.0248   0.8903
  12.750   0.8732   0.04267   0.03450   0.0438   0.0242   0.8951
  13.000   0.8861   0.04384   0.03579   0.0445   0.0234   0.9006
  13.250   0.8992   0.04506   0.03710   0.0451   0.0228   0.9068
  13.500   0.9118   0.04629   0.03842   0.0457   0.0223   0.9133
  13.750   0.9234   0.04762   0.03982   0.0462   0.0217   0.9215
  14.000   0.9366   0.04894   0.04122   0.0466   0.0214   0.9301
  14.250   0.9514   0.05034   0.04268   0.0467   0.0212   0.9399
  14.750   0.9823   0.05387   0.04659   0.0455   0.0205   0.9652
  15.250   0.9990   0.05791   0.05098   0.0457   0.0201   1.0000
  15.500   1.0037   0.06039   0.05365   0.0458   0.0198   1.0000
  15.750   1.0069   0.06309   0.05654   0.0458   0.0196   1.0000
  16.000   1.0081   0.06600   0.05962   0.0457   0.0195   1.0000
  16.250   1.0058   0.06930   0.06312   0.0455   0.0192   1.0000
  16.500   1.0019   0.07288   0.06692   0.0450   0.0192   1.0000
  16.750   0.9952   0.07689   0.07113   0.0443   0.0191   1.0000
  17.000   0.9857   0.08141   0.07586   0.0432   0.0190   1.0000
  17.250   0.9737   0.08646   0.08113   0.0417   0.0189   1.0000
  17.500   0.9582   0.09224   0.08714   0.0395   0.0189   1.0000
  17.750   0.9398   0.09882   0.09395   0.0366   0.0189   1.0000
  18.000   0.9170   0.10657   0.10195   0.0328   0.0190   1.0000
  18.250   0.8880   0.11608   0.11171   0.0274   0.0190   1.0000
  18.500   0.8390   0.13099   0.12695   0.0185   0.0193   1.0000
<< Back to NACA 66(3)-218 (naca663218-il)

Polar data table (+)

Polar graphs


<< Back to NACA 66(3)-218 (naca663218-il)