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(4)-221 (naca664221-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(4)-221 (naca664221-il)
Reynolds number: 100,000
Max Cl/Cd: 18.07 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca664221-il-100000-n5.txt
Download as CSV file: xf-naca664221-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(4)-221                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.5636   0.10668   0.10074  -0.0994   0.9600   0.0372
 -17.250  -0.5891   0.09776   0.09160  -0.1054   0.9549   0.0370
 -17.000  -0.6180   0.08940   0.08294  -0.1105   0.9496   0.0369
 -16.750  -0.6429   0.08240   0.07562  -0.1145   0.9447   0.0370
 -16.500  -0.6627   0.07694   0.06987  -0.1166   0.9385   0.0370
 -16.250  -0.6781   0.07231   0.06494  -0.1181   0.9329   0.0371
 -16.000  -0.6934   0.06819   0.06048  -0.1188   0.9274   0.0372
 -15.750  -0.7008   0.06495   0.05701  -0.1188   0.9214   0.0374
 -15.500  -0.6982   0.06238   0.05426  -0.1189   0.9164   0.0377
 -15.250  -0.6953   0.06002   0.05173  -0.1188   0.9115   0.0379
 -15.000  -0.6917   0.05785   0.04939  -0.1183   0.9061   0.0382
 -14.750  -0.6854   0.05584   0.04720  -0.1179   0.9014   0.0386
 -14.500  -0.6771   0.05396   0.04513  -0.1175   0.8975   0.0390
 -14.250  -0.6677   0.05223   0.04324  -0.1170   0.8929   0.0396
 -14.000  -0.6554   0.05063   0.04146  -0.1165   0.8886   0.0401
 -13.750  -0.6406   0.04916   0.03981  -0.1162   0.8850   0.0407
 -13.500  -0.6264   0.04772   0.03814  -0.1157   0.8818   0.0419
 -13.250  -0.6097   0.04647   0.03671  -0.1154   0.8790   0.0429
 -13.000  -0.5890   0.04551   0.03577  -0.1155   0.8757   0.0439
 -12.750  -0.5711   0.04457   0.03479  -0.1152   0.8724   0.0452
 -12.500  -0.5512   0.04368   0.03381  -0.1150   0.8694   0.0465
 -12.250  -0.5303   0.04285   0.03287  -0.1148   0.8668   0.0479
 -12.000  -0.5097   0.04208   0.03203  -0.1145   0.8644   0.0491
 -11.750  -0.4929   0.04122   0.03119  -0.1141   0.8622   0.0508
 -11.500  -0.4765   0.04044   0.03037  -0.1136   0.8598   0.0527
 -11.250  -0.4604   0.03971   0.02955  -0.1131   0.8570   0.0552
 -11.000  -0.4472   0.03886   0.02873  -0.1123   0.8541   0.0573
 -10.750  -0.4341   0.03806   0.02791  -0.1114   0.8514   0.0601
 -10.500  -0.4209   0.03730   0.02707  -0.1104   0.8487   0.0631
 -10.250  -0.4098   0.03644   0.02620  -0.1092   0.8464   0.0664
 -10.000  -0.3969   0.03569   0.02536  -0.1081   0.8443   0.0714
  -9.750  -0.3862   0.03485   0.02456  -0.1067   0.8423   0.0775
  -9.500  -0.3754   0.03416   0.02392  -0.1055   0.8398   0.0857
  -9.250  -0.3651   0.03345   0.02332  -0.1041   0.8373   0.1000
  -9.000  -0.3566   0.03266   0.02276  -0.1024   0.8349   0.1303
  -8.750  -0.3511   0.03175   0.02224  -0.1004   0.8326   0.1858
  -8.500  -0.3489   0.03082   0.02170  -0.0978   0.8304   0.2515
  -8.250  -0.3473   0.02999   0.02124  -0.0950   0.8283   0.3167
  -8.000  -0.3414   0.02950   0.02116  -0.0922   0.8266   0.3861
  -7.750  -0.3129   0.03028   0.02235  -0.0912   0.8255   0.4631
  -7.500  -0.2678   0.03220   0.02446  -0.0916   0.8247   0.5185
  -7.250  -0.2418   0.03364   0.02592  -0.0902   0.8232   0.5563
  -7.000  -0.2213   0.03520   0.02745  -0.0881   0.8207   0.5795
  -6.750  -0.2048   0.03613   0.02832  -0.0861   0.8180   0.5954
  -6.500  -0.1921   0.03657   0.02867  -0.0840   0.8157   0.6075
  -6.250  -0.1861   0.03680   0.02883  -0.0812   0.8134   0.6205
  -5.750  -0.1501   0.03771   0.02956  -0.0784   0.8102   0.6380
  -5.500  -0.1438   0.03788   0.02964  -0.0754   0.8085   0.6496
  -5.250  -0.1156   0.03837   0.03003  -0.0755   0.8075   0.6547
  -4.750  -0.0844   0.03884   0.03034  -0.0722   0.8051   0.6705
  -4.250  -0.1159   0.04093   0.03250  -0.0587   0.7960   0.6872
  -4.000  -0.0905   0.04157   0.03308  -0.0584   0.7945   0.6905
  -3.750  -0.1090   0.04186   0.03336  -0.0513   0.7915   0.7018
  -3.500  -0.0831   0.04209   0.03351  -0.0512   0.7901   0.7057
  -3.250  -0.0507   0.04234   0.03369  -0.0522   0.7891   0.7087
  -3.000  -0.0746   0.04215   0.03346  -0.0442   0.7870   0.7211
  -1.500  -0.2068   0.04445   0.03580   0.0045   0.7598   0.7596
  -1.250  -0.1820   0.04473   0.03603   0.0046   0.7572   0.7615
  -1.000  -0.1559   0.04487   0.03614   0.0045   0.7550   0.7638
  -0.750  -0.1343   0.04487   0.03609   0.0051   0.7531   0.7669
  -0.250  -0.1745   0.04393   0.03510   0.0197   0.7431   0.7796
   0.000  -0.1578   0.04404   0.03518   0.0210   0.7394   0.7815
   0.250  -0.1365   0.04396   0.03507   0.0216   0.7366   0.7835
   0.500  -0.1138   0.04380   0.03487   0.0220   0.7345   0.7858
   0.750  -0.0904   0.04352   0.03456   0.0222   0.7328   0.7883
   1.000  -0.1338   0.04274   0.03374   0.0325   0.7231   0.7955
   1.250  -0.1184   0.04237   0.03334   0.0337   0.7195   0.7976
   1.500  -0.0911   0.04232   0.03328   0.0334   0.7172   0.7988
   1.750  -0.0612   0.04221   0.03316   0.0326   0.7154   0.8000
   2.250  -0.0488   0.04227   0.03323   0.0379   0.7028   0.8033
   2.500  -0.0232   0.04212   0.03307   0.0377   0.7001   0.8049
   2.750   0.0059   0.04192   0.03287   0.0370   0.6981   0.8065
   3.250   0.0229   0.04185   0.03281   0.0410   0.6849   0.8105
   3.500   0.0515   0.04157   0.03254   0.0403   0.6822   0.8119
   3.750   0.0828   0.04126   0.03224   0.0391   0.6803   0.8132
   4.000   0.0793   0.04150   0.03248   0.0422   0.6693   0.8159
   4.250   0.1080   0.04136   0.03238   0.0418   0.6661   0.8169
   4.500   0.1399   0.04115   0.03222   0.0409   0.6639   0.8179
   4.750   0.1416   0.04159   0.03271   0.0437   0.6531   0.8194
   5.000   0.1707   0.04138   0.03255   0.0431   0.6496   0.8204
   5.250   0.2038   0.04105   0.03228   0.0421   0.6473   0.8215
   5.500   0.2067   0.04150   0.03279   0.0446   0.6357   0.8232
   5.750   0.2379   0.04118   0.03253   0.0438   0.6325   0.8244
   6.250   0.2759   0.04122   0.03271   0.0448   0.6178   0.8276
   6.750   0.3177   0.04114   0.03276   0.0454   0.6029   0.8310
   7.250   0.3629   0.04089   0.03267   0.0456   0.5876   0.8349
   7.750   0.4076   0.04049   0.03250   0.0466   0.5719   0.8379
   8.250   0.4543   0.03992   0.03216   0.0474   0.5556   0.8411
   8.750   0.5043   0.03907   0.03155   0.0480   0.5376   0.8448
   9.000   0.5264   0.03868   0.03126   0.0486   0.5222   0.8469
   9.250   0.5571   0.03736   0.02995   0.0490   0.4975   0.8489
   9.500   0.5880   0.03611   0.02857   0.0494   0.4574   0.8511
   9.750   0.6192   0.03513   0.02735   0.0496   0.4096   0.8530
  10.000   0.6365   0.03523   0.02726   0.0509   0.3657   0.8549
  10.250   0.6468   0.03589   0.02767   0.0526   0.3187   0.8570
  10.500   0.6522   0.03700   0.02853   0.0544   0.2713   0.8594
  10.750   0.6562   0.03834   0.02960   0.0561   0.2241   0.8621
  11.000   0.6582   0.03992   0.03089   0.0577   0.1747   0.8652
  11.250   0.6615   0.04157   0.03223   0.0591   0.1305   0.8683
  11.500   0.6662   0.04318   0.03360   0.0602   0.1000   0.8712
  11.750   0.6723   0.04462   0.03496   0.0615   0.0835   0.8739
  12.000   0.6791   0.04608   0.03639   0.0626   0.0730   0.8769
  12.250   0.6869   0.04753   0.03783   0.0634   0.0666   0.8801
  12.500   0.6951   0.04904   0.03937   0.0641   0.0609   0.8835
  12.750   0.7041   0.05055   0.04092   0.0646   0.0570   0.8869
  13.000   0.7118   0.05206   0.04249   0.0653   0.0535   0.8901
  13.250   0.7199   0.05356   0.04407   0.0660   0.0508   0.8936
  13.500   0.7292   0.05504   0.04562   0.0665   0.0485   0.8975
  13.750   0.7384   0.05658   0.04718   0.0668   0.0468   0.9018
  14.000   0.7487   0.05804   0.04874   0.0672   0.0446   0.9059
  14.250   0.7598   0.05939   0.05019   0.0676   0.0431   0.9103
  14.500   0.7715   0.06078   0.05162   0.0678   0.0417   0.9154
  14.750   0.7839   0.06214   0.05296   0.0679   0.0406   0.9207
  15.000   0.7979   0.06344   0.05444   0.0681   0.0391   0.9263
  15.250   0.8110   0.06489   0.05601   0.0680   0.0377   0.9331
  15.500   0.8249   0.06640   0.05761   0.0676   0.0366   0.9400
  15.750   0.8406   0.06787   0.05911   0.0669   0.0356   0.9480
  16.000   0.8587   0.06947   0.06084   0.0659   0.0349   0.9562
  16.250   0.8744   0.07147   0.06308   0.0647   0.0341   0.9663
  16.500   0.8847   0.07333   0.06515   0.0639   0.0335   1.0000
  16.750   0.8940   0.07571   0.06768   0.0633   0.0330   1.0000
  17.000   0.9013   0.07831   0.07043   0.0625   0.0326   1.0000
  17.250   0.9060   0.08118   0.07348   0.0617   0.0322   1.0000
  17.500   0.9087   0.08432   0.07678   0.0608   0.0319   1.0000
  17.750   0.9095   0.08764   0.08025   0.0597   0.0316   1.0000
  18.000   0.9087   0.09121   0.08397   0.0584   0.0313   1.0000
  18.250   0.9064   0.09501   0.08791   0.0570   0.0311   1.0000
  18.500   0.9059   0.09860   0.09160   0.0555   0.0307   1.0000
  18.750   0.8940   0.10381   0.09702   0.0533   0.0306   1.0000
  19.000   0.8722   0.11068   0.10418   0.0500   0.0304   1.0000
<< Back to NACA 66(4)-221 (naca664221-il)

Polar data table (+)

Polar graphs


<< Back to NACA 66(4)-221 (naca664221-il)