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NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NLR-7223-62 AIRFOIL (nl722362-il)
Reynolds number: 100,000
Max Cl/Cd: 39.78 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nl722362-il-100000-n5.txt
Download as CSV file: xf-nl722362-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7223-62 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4929   0.09075   0.08575  -0.0304   1.0000   0.0543
  -8.750  -0.4964   0.08681   0.08187  -0.0321   1.0000   0.0551
  -8.500  -0.5038   0.08285   0.07798  -0.0345   1.0000   0.0553
  -8.250  -0.5160   0.07933   0.07451  -0.0351   1.0000   0.0555
  -8.000  -0.5296   0.07634   0.07156  -0.0339   1.0000   0.0558
  -7.750  -0.5420   0.07333   0.06855  -0.0324   1.0000   0.0560
  -7.500  -0.5541   0.07063   0.06583  -0.0300   1.0000   0.0564
  -7.250  -0.5655   0.06796   0.06312  -0.0272   1.0000   0.0564
  -7.000  -0.5870   0.06202   0.05680  -0.0238   1.0000   0.0421
  -6.500  -0.5976   0.05185   0.04587  -0.0159   1.0000   0.0257
  -6.250  -0.5943   0.04916   0.04307  -0.0132   1.0000   0.0253
  -6.000  -0.5903   0.04635   0.04005  -0.0104   1.0000   0.0250
  -5.750  -0.5842   0.04364   0.03711  -0.0076   1.0000   0.0247
  -5.500  -0.5766   0.04081   0.03396  -0.0047   1.0000   0.0244
  -5.250  -0.5669   0.03805   0.03084  -0.0019   1.0000   0.0243
  -5.000  -0.5502   0.03535   0.02770  -0.0001   0.9987   0.0246
  -4.750  -0.5296   0.03283   0.02450   0.0016   0.9967   0.0257
  -4.500  -0.5075   0.03045   0.02176   0.0024   0.9950   0.0262
  -4.250  -0.4840   0.02842   0.01936   0.0034   0.9933   0.0263
  -4.000  -0.4601   0.02664   0.01728   0.0042   0.9918   0.0266
  -3.750  -0.4344   0.02513   0.01555   0.0047   0.9902   0.0270
  -3.500  -0.4071   0.02384   0.01408   0.0049   0.9885   0.0276
  -3.250  -0.3789   0.02267   0.01276   0.0050   0.9868   0.0287
  -3.000  -0.3500   0.02184   0.01177   0.0049   0.9850   0.0317
  -2.750  -0.3254   0.02089   0.01081   0.0055   0.9827   0.0336
  -2.500  -0.3005   0.02008   0.01001   0.0060   0.9801   0.0359
  -2.250  -0.2742   0.01948   0.00931   0.0063   0.9774   0.0385
  -2.000  -0.2460   0.01892   0.00870   0.0061   0.9747   0.0444
  -1.750  -0.2191   0.01844   0.00819   0.0063   0.9717   0.0545
  -1.500  -0.0728   0.01557   0.00878  -0.0161   0.9927   1.0000
  -1.250  -0.0425   0.01561   0.00860  -0.0171   0.9886   1.0000
  -1.000  -0.0097   0.01570   0.00849  -0.0185   0.9849   1.0000
  -0.750   0.0199   0.01572   0.00836  -0.0193   0.9797   1.0000
  -0.500   0.0560   0.01581   0.00832  -0.0214   0.9748   1.0000
  -0.250   0.0907   0.01584   0.00824  -0.0231   0.9678   1.0000
   0.000   0.1472   0.01576   0.00806  -0.0289   0.9570   1.0000
   0.250   0.2617   0.01470   0.00691  -0.0449   0.9277   1.0000
   0.500   0.3050   0.01434   0.00652  -0.0475   0.9121   1.0000
   0.750   0.3393   0.01414   0.00630  -0.0485   0.8998   1.0000
   1.000   0.3663   0.01400   0.00616  -0.0480   0.8859   1.0000
   1.250   0.3924   0.01385   0.00602  -0.0472   0.8701   1.0000
   1.500   0.4130   0.01375   0.00595  -0.0453   0.8508   1.0000
   1.750   0.4339   0.01363   0.00585  -0.0435   0.8278   1.0000
   2.000   0.4523   0.01355   0.00580  -0.0411   0.7980   1.0000
   2.250   0.4648   0.01357   0.00586  -0.0378   0.7371   1.0000
   2.500   0.5041   0.01324   0.00468  -0.0377   0.5718   1.0000
   2.750   0.5201   0.01395   0.00479  -0.0352   0.4606   1.0000
   3.000   0.5371   0.01461   0.00502  -0.0331   0.3811   1.0000
   3.250   0.5560   0.01518   0.00529  -0.0315   0.3265   1.0000
   3.500   0.5760   0.01569   0.00559  -0.0301   0.2912   1.0000
   3.750   0.5967   0.01614   0.00594  -0.0288   0.2684   1.0000
   4.000   0.6175   0.01658   0.00631  -0.0275   0.2521   1.0000
   4.250   0.6384   0.01702   0.00669  -0.0263   0.2392   1.0000
   4.500   0.6592   0.01750   0.00713  -0.0250   0.2281   1.0000
   4.750   0.6807   0.01791   0.00757  -0.0238   0.2180   1.0000
   5.000   0.7017   0.01839   0.00803  -0.0226   0.2092   1.0000
   5.250   0.7230   0.01885   0.00852  -0.0215   0.2007   1.0000
   5.500   0.7443   0.01934   0.00907  -0.0203   0.1929   1.0000
   5.750   0.7655   0.01982   0.00959  -0.0192   0.1849   1.0000
   6.000   0.7868   0.02034   0.01018  -0.0180   0.1772   1.0000
   6.250   0.8074   0.02085   0.01073  -0.0168   0.1690   1.0000
   6.500   0.8284   0.02135   0.01140  -0.0156   0.1602   1.0000
   6.750   0.8480   0.02187   0.01195  -0.0143   0.1511   1.0000
   7.000   0.8668   0.02223   0.01242  -0.0128   0.1388   1.0000
   7.250   0.8852   0.02252   0.01283  -0.0113   0.1245   1.0000
   7.500   0.9047   0.02285   0.01333  -0.0099   0.1090   1.0000
   7.750   0.9242   0.02323   0.01383  -0.0085   0.0909   1.0000
   8.000   0.9414   0.02392   0.01448  -0.0069   0.0742   1.0000
   8.250   0.9567   0.02496   0.01552  -0.0050   0.0604   1.0000
   8.500   0.9704   0.02619   0.01679  -0.0029   0.0518   1.0000
   8.750   0.9826   0.02747   0.01809  -0.0006   0.0459   1.0000
   9.000   0.9959   0.02865   0.01944   0.0016   0.0411   1.0000
   9.250   1.0059   0.02999   0.02085   0.0041   0.0383   1.0000
   9.500   1.0161   0.03142   0.02249   0.0067   0.0363   1.0000
   9.750   1.0258   0.03285   0.02411   0.0092   0.0342   1.0000
  10.000   1.0340   0.03421   0.02560   0.0118   0.0324   1.0000
  10.250   1.0401   0.03569   0.02717   0.0145   0.0312   1.0000
  10.500   1.0452   0.03739   0.02904   0.0174   0.0300   1.0000
  10.750   1.0480   0.03914   0.03106   0.0205   0.0289   1.0000
  11.000   1.0483   0.04098   0.03313   0.0239   0.0282   1.0000
  11.250   1.0467   0.04299   0.03537   0.0270   0.0277   1.0000
  11.500   1.0432   0.04517   0.03777   0.0300   0.0272   1.0000
  11.750   1.0379   0.04755   0.04037   0.0327   0.0267   1.0000
  12.000   1.0306   0.05017   0.04320   0.0349   0.0264   1.0000
  12.250   1.0210   0.05313   0.04638   0.0367   0.0262   1.0000
  12.500   1.0085   0.05654   0.05000   0.0377   0.0260   1.0000
  12.750   0.9938   0.06048   0.05414   0.0379   0.0258   1.0000
  13.000   0.9742   0.06560   0.05951   0.0365   0.0260   1.0000
  13.250   0.9504   0.07227   0.06640   0.0330   0.0260   1.0000
  13.500   0.9152   0.08279   0.07718   0.0256   0.0265   1.0000
  13.750   0.8534   0.10196   0.09655   0.0125   0.0278   1.0000
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