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NACA 64(3)-218 (naca643218-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(3)-218 (naca643218-il)
Reynolds number: 50,000
Max Cl/Cd: 21.94 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca643218-il-50000.txt
Download as CSV file: xf-naca643218-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(3)-218                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5664   0.10016   0.09271  -0.0472   1.0000   0.1580
 -12.250  -0.7313   0.07852   0.07088  -0.0609   1.0000   0.1420
 -12.000  -0.7513   0.07348   0.06577  -0.0614   1.0000   0.1413
 -11.750  -0.7733   0.06908   0.06126  -0.0611   1.0000   0.1407
 -11.500  -0.7957   0.06537   0.05744  -0.0597   1.0000   0.1402
 -11.250  -0.8183   0.06229   0.05423  -0.0570   1.0000   0.1399
 -11.000  -0.8354   0.05940   0.05116  -0.0543   1.0000   0.1398
 -10.750  -0.8512   0.05687   0.04844  -0.0508   1.0000   0.1399
 -10.500  -0.8671   0.05479   0.04619  -0.0466   1.0000   0.1401
 -10.250  -0.8839   0.05310   0.04430  -0.0418   1.0000   0.1407
 -10.000  -0.8996   0.05156   0.04252  -0.0369   1.0000   0.1414
  -9.750  -0.9015   0.04947   0.04035  -0.0337   1.0000   0.1434
  -9.500  -0.8932   0.04768   0.03860  -0.0315   1.0000   0.1471
  -9.250  -0.8912   0.04611   0.03693  -0.0285   1.0000   0.1505
  -9.000  -0.8902   0.04451   0.03508  -0.0254   1.0000   0.1536
  -8.750  -0.8907   0.04304   0.03325  -0.0222   1.0000   0.1570
  -8.500  -0.8701   0.04133   0.03176  -0.0212   1.0000   0.1645
  -8.250  -0.8616   0.04005   0.03027  -0.0189   1.0000   0.1716
  -8.000  -0.8395   0.03867   0.02909  -0.0178   1.0000   0.1822
  -7.750  -0.8233   0.03748   0.02801  -0.0161   1.0000   0.1955
  -7.500  -0.8095   0.03635   0.02703  -0.0140   1.0000   0.2123
  -7.250  -0.8024   0.03515   0.02604  -0.0112   1.0000   0.2339
  -7.000  -0.8017   0.03372   0.02499  -0.0078   1.0000   0.2621
  -6.750  -0.8082   0.03195   0.02385  -0.0037   1.0000   0.3071
  -6.500  -0.8147   0.03177   0.02518   0.0029   1.0000   0.4190
  -6.250  -0.8077   0.03534   0.02890   0.0105   1.0000   0.5190
  -6.000  -0.7907   0.03925   0.03269   0.0169   1.0000   0.5607
  -5.750  -0.7548   0.04484   0.03814   0.0233   1.0000   0.5891
  -5.500  -0.6672   0.05301   0.04596   0.0254   0.9956   0.6233
  -5.250  -0.4921   0.06065   0.05292   0.0149   0.9897   0.6764
  -5.000  -0.4089   0.06171   0.05364   0.0083   0.9835   0.7129
  -4.750  -0.3715   0.06154   0.05327   0.0058   0.9764   0.7392
  -4.500  -0.2948   0.06118   0.05264  -0.0019   0.9710   0.7700
  -4.250  -0.2616   0.06058   0.05189  -0.0043   0.9643   0.7907
  -4.000  -0.2197   0.05988   0.05102  -0.0087   0.9582   0.8110
  -3.750  -0.1883   0.05913   0.05015  -0.0112   0.9515   0.8265
  -3.500  -0.1496   0.05831   0.04919  -0.0154   0.9451   0.8413
  -3.250  -0.1439   0.05794   0.04874  -0.0145   0.9391   0.8465
  -3.000  -0.1528   0.05773   0.04849  -0.0113   0.9336   0.8492
  -2.750  -0.1024   0.05691   0.04755  -0.0173   0.9285   0.8607
  -2.500  -0.1068   0.05673   0.04732  -0.0146   0.9235   0.8628
  -2.250  -0.1170   0.05657   0.04713  -0.0108   0.9186   0.8650
  -2.000  -0.1261   0.05641   0.04694  -0.0073   0.9149   0.8669
  -1.750  -0.0839   0.05602   0.04645  -0.0121   0.9113   0.8736
  -1.500  -0.0902   0.05591   0.04632  -0.0089   0.9091   0.8759
  -1.250  -0.1046   0.05575   0.04615  -0.0043   0.9072   0.8785
  -1.000  -0.1217   0.05553   0.04592   0.0007   0.9063   0.8811
  -0.750  -0.1439   0.05528   0.04566   0.0066   0.9079   0.8844
  -0.500  -0.1302   0.05511   0.04546   0.0065   0.9076   0.8885
  -0.250  -0.1296   0.05497   0.04529   0.0086   0.9086   0.8927
   0.000  -0.1733   0.05412   0.04447   0.0180   0.9191   0.8969
   0.250  -0.2610   0.05214   0.04256   0.0351   0.9546   0.9021
   0.500  -0.3686   0.04786   0.03837   0.0578   1.0000   0.9095
   0.750  -0.3713   0.04705   0.03752   0.0607   1.0000   0.9172
   1.000  -0.3424   0.04728   0.03770   0.0578   1.0000   0.9223
   1.250  -0.3305   0.04703   0.03740   0.0580   1.0000   0.9297
   1.500  -0.3008   0.04744   0.03778   0.0548   1.0000   0.9359
   1.750  -0.2759   0.04777   0.03808   0.0524   1.0000   0.9431
   2.000  -0.2472   0.04827   0.03856   0.0491   1.0000   0.9495
   2.250  -0.2176   0.04891   0.03918   0.0457   1.0000   0.9567
   2.500  -0.1822   0.04983   0.04010   0.0410   1.0000   0.9638
   2.750  -0.1490   0.05080   0.04108   0.0366   1.0000   0.9722
   3.000  -0.1113   0.05198   0.04228   0.0311   1.0000   0.9800
   3.250  -0.0757   0.05316   0.04349   0.0259   1.0000   0.9883
   3.500  -0.0378   0.05468   0.04504   0.0201   1.0000   0.9990
   3.750  -0.0380   0.05436   0.04473   0.0215   1.0000   1.0000
   4.000  -0.0184   0.05513   0.04552   0.0190   0.9916   1.0000
   4.250   0.0128   0.05663   0.04706   0.0144   0.9733   1.0000
   4.500   0.0353   0.05806   0.04850   0.0117   0.9571   1.0000
   4.750   0.0460   0.05828   0.04874   0.0114   0.9398   1.0000
   5.000   0.0559   0.05869   0.04915   0.0113   0.9226   1.0000
   5.250   0.0697   0.05954   0.04999   0.0105   0.9071   1.0000
   5.500   0.0961   0.06153   0.05199   0.0076   0.8925   1.0000
   5.750   0.1253   0.06360   0.05408   0.0043   0.8763   1.0000
   6.000   0.1460   0.06479   0.05529   0.0026   0.8598   1.0000
   6.250   0.1676   0.06629   0.05682   0.0007   0.8432   1.0000
   6.500   0.1892   0.06799   0.05856  -0.0011   0.8267   1.0000
   6.750   0.2119   0.06994   0.06055  -0.0031   0.8098   1.0000
   7.000   0.2348   0.07202   0.06268  -0.0050   0.7926   1.0000
   7.250   0.2577   0.07420   0.06493  -0.0069   0.7748   1.0000
   7.500   0.2819   0.07649   0.06728  -0.0087   0.7552   1.0000
   7.750   0.3098   0.07902   0.06989  -0.0108   0.7341   1.0000
   8.000   0.3491   0.08259   0.07357  -0.0140   0.7114   1.0000
   8.250   0.3836   0.08434   0.07542  -0.0152   0.6755   1.0000
   8.500   0.4870   0.07831   0.06958  -0.0126   0.5681   1.0000
   8.750   0.4988   0.07922   0.07057  -0.0118   0.5430   1.0000
   9.000   0.5559   0.07789   0.06944  -0.0116   0.5161   1.0000
   9.250   0.5686   0.07861   0.07026  -0.0106   0.4908   1.0000
   9.500   0.6331   0.07493   0.06686  -0.0090   0.4650   1.0000
   9.750   0.6563   0.07399   0.06606  -0.0072   0.4378   1.0000
  10.250   0.9017   0.04168   0.03412   0.0075   0.3320   1.0000
  10.500   0.9185   0.04186   0.03334   0.0107   0.2695   1.0000
  10.750   0.9280   0.04388   0.03495   0.0125   0.2323   1.0000
  11.000   0.9535   0.04556   0.03625   0.0135   0.2017   1.0000
  11.250   0.9834   0.04741   0.03796   0.0139   0.1797   1.0000
  11.500   1.0437   0.04948   0.03967   0.0122   0.1588   1.0000
  11.750   1.0470   0.05208   0.04265   0.0135   0.1522   1.0000
  12.000   1.0846   0.05499   0.04552   0.0125   0.1427   1.0000
  12.250   1.0782   0.05794   0.04884   0.0143   0.1393   1.0000
  12.500   1.0814   0.06104   0.05217   0.0152   0.1354   1.0000
  12.750   1.1186   0.06467   0.05571   0.0141   0.1294   1.0000
  13.000   1.0992   0.06821   0.05959   0.0159   0.1288   1.0000
  13.250   1.0777   0.07225   0.06393   0.0171   0.1284   1.0000
  13.500   1.0525   0.07688   0.06884   0.0176   0.1283   1.0000
  13.750   1.0253   0.08220   0.07441   0.0173   0.1286   1.0000
  14.000   0.9948   0.08838   0.08079   0.0162   0.1290   1.0000
  14.250   0.9666   0.09526   0.08784   0.0142   0.1296   1.0000
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