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NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA NLF1015 (nlf1015-il)
Reynolds number: 200,000
Max Cl/Cd: 77.17 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf1015-il-200000-n5.txt
Download as CSV file: xf-nlf1015-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA  NLF1015                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1928   0.05712   0.05301  -0.1468   0.9140   0.0168
 -10.000  -0.2030   0.04856   0.04413  -0.1583   0.9083   0.0167
  -9.750  -0.2121   0.04420   0.03954  -0.1620   0.8981   0.0166
  -9.500  -0.2210   0.04057   0.03564  -0.1639   0.8887   0.0165
  -9.250  -0.2238   0.03720   0.03190  -0.1652   0.8807   0.0166
  -9.000  -0.2237   0.03473   0.02912  -0.1644   0.8726   0.0165
  -8.750  -0.2145   0.03209   0.02607  -0.1646   0.8669   0.0166
  -8.500  -0.2023   0.02987   0.02346  -0.1643   0.8618   0.0167
  -8.250  -0.1901   0.02816   0.02144  -0.1632   0.8561   0.0168
  -8.000  -0.1691   0.02647   0.01940  -0.1635   0.8524   0.0170
  -7.750  -0.1448   0.02466   0.01731  -0.1642   0.8495   0.0172
  -7.500  -0.1303   0.02345   0.01602  -0.1627   0.8442   0.0178
  -7.250  -0.1080   0.02252   0.01497  -0.1626   0.8403   0.0186
  -7.000  -0.0816   0.02160   0.01390  -0.1631   0.8372   0.0194
  -6.750  -0.0546   0.02064   0.01279  -0.1636   0.8345   0.0199
  -6.500  -0.0367   0.01991   0.01197  -0.1622   0.8301   0.0202
  -6.250  -0.0140   0.01917   0.01114  -0.1617   0.8266   0.0206
  -6.000   0.0113   0.01845   0.01032  -0.1618   0.8238   0.0211
  -5.750   0.0388   0.01778   0.00954  -0.1624   0.8215   0.0217
  -5.500   0.0633   0.01726   0.00893  -0.1623   0.8186   0.0223
  -5.250   0.0842   0.01674   0.00837  -0.1616   0.8147   0.0232
  -5.000   0.1098   0.01629   0.00786  -0.1618   0.8115   0.0245
  -4.750   0.1380   0.01592   0.00740  -0.1624   0.8090   0.0276
  -4.500   0.1678   0.01551   0.00694  -0.1633   0.8070   0.0318
  -4.250   0.1970   0.01511   0.00653  -0.1642   0.8049   0.0419
  -4.000   0.2197   0.01469   0.00629  -0.1638   0.8017   0.0795
  -3.750   0.2460   0.01422   0.00607  -0.1644   0.7988   0.1458
  -3.500   0.2753   0.01359   0.00584  -0.1659   0.7963   0.2522
  -3.250   0.3079   0.01280   0.00566  -0.1682   0.7942   0.4155
  -3.000   0.3379   0.01259   0.00594  -0.1688   0.7923   0.5599
  -2.750   0.3682   0.01274   0.00608  -0.1693   0.7906   0.6085
  -2.500   0.3907   0.01292   0.00624  -0.1683   0.7876   0.6267
  -2.250   0.4157   0.01308   0.00635  -0.1679   0.7849   0.6417
  -2.000   0.4427   0.01321   0.00643  -0.1678   0.7824   0.6550
  -1.750   0.4720   0.01332   0.00644  -0.1682   0.7802   0.6667
  -1.500   0.5003   0.01342   0.00651  -0.1683   0.7783   0.6753
  -1.250   0.5309   0.01352   0.00654  -0.1690   0.7767   0.6847
  -1.000   0.5555   0.01368   0.00669  -0.1685   0.7744   0.6928
  -0.750   0.5780   0.01385   0.00685  -0.1676   0.7712   0.7002
  -0.500   0.6024   0.01399   0.00699  -0.1671   0.7685   0.7063
  -0.250   0.6314   0.01409   0.00703  -0.1677   0.7664   0.7131
   0.000   0.6592   0.01416   0.00711  -0.1678   0.7644   0.7172
   0.250   0.6896   0.01422   0.00714  -0.1685   0.7626   0.7219
   0.500   0.7209   0.01429   0.00716  -0.1695   0.7609   0.7267
   0.750   0.7397   0.01450   0.00742  -0.1680   0.7573   0.7304
   1.000   0.7628   0.01464   0.00760  -0.1673   0.7542   0.7335
   1.250   0.7898   0.01474   0.00770  -0.1674   0.7516   0.7370
   1.500   0.8203   0.01478   0.00774  -0.1682   0.7493   0.7406
   1.750   0.8533   0.01481   0.00774  -0.1696   0.7474   0.7444
   2.000   0.8750   0.01497   0.00797  -0.1686   0.7440   0.7472
   2.250   0.8948   0.01516   0.00823  -0.1673   0.7398   0.7503
   2.500   0.9218   0.01523   0.00832  -0.1674   0.7365   0.7537
   2.750   0.9542   0.01522   0.00832  -0.1685   0.7337   0.7577
   3.000   0.9834   0.01525   0.00838  -0.1690   0.7306   0.7609
   3.250   0.9980   0.01548   0.00872  -0.1666   0.7250   0.7641
   3.500   1.0250   0.01549   0.00878  -0.1666   0.7209   0.7676
   3.750   1.0598   0.01540   0.00869  -0.1681   0.7175   0.7713
   4.000   1.0733   0.01563   0.00905  -0.1655   0.7112   0.7757
   4.250   1.0977   0.01564   0.00913  -0.1649   0.7060   0.7793
   4.500   1.1311   0.01553   0.00905  -0.1661   0.7019   0.7830
   4.750   1.1408   0.01579   0.00942  -0.1628   0.6942   0.7879
   5.000   1.1706   0.01567   0.00937  -0.1632   0.6886   0.7916
   5.250   1.1794   0.01586   0.00968  -0.1596   0.6805   0.7963
   5.500   1.2064   0.01577   0.00964  -0.1594   0.6735   0.8014
   5.750   1.2133   0.01603   0.01003  -0.1555   0.6641   0.8071
   6.000   1.2327   0.01607   0.01015  -0.1539   0.6552   0.8122
   6.250   1.2494   0.01619   0.01037  -0.1518   0.6445   0.8183
   6.500   1.2589   0.01647   0.01076  -0.1485   0.6320   0.8242
   6.750   1.2715   0.01670   0.01107  -0.1458   0.6174   0.8310
   7.000   1.2858   0.01689   0.01131  -0.1433   0.5996   0.8382
   7.250   1.2976   0.01716   0.01158  -0.1404   0.5737   0.8463
   7.500   1.3088   0.01748   0.01177  -0.1374   0.5358   0.8546
   8.000   1.3034   0.01956   0.01332  -0.1273   0.4422   0.8764
   8.250   1.2947   0.02101   0.01457  -0.1218   0.3997   0.8914
   8.500   1.2852   0.02249   0.01589  -0.1164   0.3623   0.9145
   8.750   1.2760   0.02389   0.01716  -0.1113   0.3266   1.0000
   9.000   1.2740   0.02583   0.01888  -0.1082   0.2879   1.0000
   9.250   1.2746   0.02771   0.02057  -0.1056   0.2513   1.0000
   9.500   1.2749   0.02970   0.02237  -0.1031   0.2154   1.0000
   9.750   1.2763   0.03170   0.02417  -0.1008   0.1793   1.0000
  10.000   1.2801   0.03360   0.02590  -0.0989   0.1490   1.0000
  10.250   1.2839   0.03556   0.02769  -0.0971   0.1192   1.0000
  10.500   1.2876   0.03759   0.02955  -0.0954   0.0913   1.0000
  10.750   1.2933   0.03950   0.03134  -0.0939   0.0690   1.0000
  11.000   1.2987   0.04149   0.03324  -0.0924   0.0492   1.0000
  11.250   1.3031   0.04364   0.03529  -0.0910   0.0325   1.0000
  11.500   1.3076   0.04582   0.03744  -0.0896   0.0218   1.0000
  11.750   1.3145   0.04783   0.03948  -0.0884   0.0174   1.0000
  12.000   1.3220   0.04982   0.04153  -0.0874   0.0151   1.0000
  12.250   1.3296   0.05183   0.04362  -0.0865   0.0136   1.0000
  12.500   1.3361   0.05399   0.04587  -0.0855   0.0127   1.0000
  12.750   1.3423   0.05622   0.04821  -0.0847   0.0121   1.0000
  13.000   1.3486   0.05849   0.05062  -0.0839   0.0117   1.0000
  13.250   1.3540   0.06090   0.05316  -0.0831   0.0113   1.0000
  13.500   1.3583   0.06348   0.05589  -0.0825   0.0110   1.0000
  13.750   1.3618   0.06620   0.05874  -0.0819   0.0107   1.0000
  14.000   1.3646   0.06905   0.06173  -0.0813   0.0104   1.0000
  14.250   1.3665   0.07208   0.06488  -0.0809   0.0102   1.0000
  14.500   1.3677   0.07525   0.06818  -0.0806   0.0100   1.0000
  14.750   1.3684   0.07857   0.07161  -0.0805   0.0098   1.0000
  15.000   1.3683   0.08202   0.07518  -0.0804   0.0096   1.0000
  15.250   1.3676   0.08561   0.07889  -0.0804   0.0095   1.0000
  15.500   1.3664   0.08932   0.08271  -0.0806   0.0093   1.0000
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