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HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il)
Reynolds number: 100,000
Max Cl/Cd: 37.38 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hsnlf213-il-100000-n5.txt
Download as CSV file: xf-hsnlf213-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HSNLF(1)-0213 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.3962   0.13727   0.13279  -0.0173   0.9146   0.0543
 -13.000  -0.4017   0.13156   0.12702  -0.0193   0.9115   0.0381
 -12.500  -0.5569   0.13025   0.12562  -0.0086   1.0000   0.0328
 -12.250  -0.5505   0.12678   0.12215  -0.0098   0.9613   0.0320
 -12.000  -0.5483   0.12232   0.11767  -0.0119   0.9385   0.0312
 -11.750  -0.5491   0.11725   0.11259  -0.0143   0.9269   0.0304
 -11.250  -0.5870   0.09305   0.08838  -0.0307   0.9136   0.0267
 -11.000  -0.5954   0.08667   0.08194  -0.0350   0.9076   0.0265
 -10.750  -0.6085   0.08049   0.07567  -0.0390   0.9019   0.0263
 -10.500  -0.6247   0.07499   0.07004  -0.0417   0.8967   0.0261
 -10.250  -0.6414   0.07002   0.06490  -0.0434   0.8918   0.0260
 -10.000  -0.6571   0.06555   0.06023  -0.0442   0.8866   0.0259
  -9.750  -0.6720   0.06165   0.05609  -0.0433   0.8818   0.0258
  -9.500  -0.6826   0.05775   0.05189  -0.0421   0.8776   0.0258
  -9.250  -0.6880   0.05368   0.04744  -0.0409   0.8733   0.0258
  -9.000  -0.6905   0.04963   0.04289  -0.0392   0.8696   0.0263
  -8.750  -0.6876   0.04611   0.03887  -0.0376   0.8665   0.0270
  -8.500  -0.6720   0.04445   0.03713  -0.0372   0.8640   0.0280
  -8.250  -0.6569   0.04216   0.03458  -0.0367   0.8612   0.0289
  -8.000  -0.6416   0.03939   0.03140  -0.0358   0.8584   0.0294
  -7.750  -0.6238   0.03684   0.02842  -0.0349   0.8557   0.0300
  -7.500  -0.6037   0.03453   0.02571  -0.0341   0.8531   0.0307
  -7.250  -0.5815   0.03251   0.02328  -0.0333   0.8508   0.0319
  -7.000  -0.5575   0.03081   0.02124  -0.0329   0.8485   0.0337
  -6.750  -0.5324   0.02958   0.01997  -0.0331   0.8462   0.0356
  -6.500  -0.5061   0.02827   0.01851  -0.0331   0.8441   0.0372
  -6.250  -0.4796   0.02702   0.01711  -0.0329   0.8420   0.0390
  -6.000  -0.4538   0.02597   0.01592  -0.0327   0.8399   0.0418
  -5.750  -0.4300   0.02509   0.01508  -0.0324   0.8378   0.0449
  -5.500  -0.4062   0.02426   0.01418  -0.0317   0.8358   0.0479
  -5.250  -0.3831   0.02348   0.01334  -0.0311   0.8338   0.0517
  -5.000  -0.3596   0.02281   0.01268  -0.0310   0.8316   0.0571
  -4.750  -0.3363   0.02219   0.01200  -0.0306   0.8294   0.0631
  -4.500  -0.3134   0.02162   0.01144  -0.0301   0.8271   0.0732
  -4.250  -0.2908   0.02104   0.01089  -0.0295   0.8248   0.0887
  -4.000  -0.2698   0.02032   0.01044  -0.0286   0.8226   0.1286
  -3.750  -0.2557   0.01908   0.01006  -0.0269   0.8206   0.2878
  -3.500  -0.2501   0.01855   0.01144  -0.0206   0.8189   0.6203
  -3.250  -0.2313   0.01935   0.01213  -0.0189   0.8160   0.7355
  -3.000  -0.2119   0.02001   0.01264  -0.0166   0.8132   0.7725
  -2.750  -0.1896   0.02103   0.01366  -0.0127   0.8110   0.8054
  -2.500  -0.1617   0.02204   0.01463  -0.0093   0.8095   0.8373
  -2.250  -0.1328   0.02232   0.01479  -0.0085   0.8078   0.8515
  -2.000  -0.1062   0.02228   0.01461  -0.0084   0.8058   0.8562
  -1.750  -0.0867   0.02219   0.01439  -0.0074   0.8036   0.8622
  -1.500  -0.0576   0.02226   0.01437  -0.0081   0.8009   0.8656
  -1.250  -0.0299   0.02231   0.01434  -0.0084   0.7980   0.8696
  -1.000  -0.0062   0.02230   0.01426  -0.0082   0.7951   0.8735
  -0.750   0.0138   0.02226   0.01414  -0.0073   0.7925   0.8775
  -0.500   0.0398   0.02222   0.01403  -0.0073   0.7903   0.8795
  -0.250   0.0663   0.02225   0.01401  -0.0075   0.7877   0.8815
   0.000   0.0902   0.02239   0.01413  -0.0076   0.7835   0.8838
   0.250   0.1141   0.02244   0.01415  -0.0075   0.7798   0.8860
   0.500   0.1383   0.02245   0.01413  -0.0072   0.7769   0.8881
   0.750   0.1626   0.02242   0.01407  -0.0068   0.7743   0.8901
   1.000   0.1824   0.02259   0.01425  -0.0063   0.7691   0.8922
   1.250   0.2045   0.02268   0.01434  -0.0059   0.7644   0.8941
   1.500   0.2314   0.02267   0.01434  -0.0059   0.7610   0.8953
   1.750   0.2590   0.02261   0.01428  -0.0059   0.7583   0.8962
   2.000   0.2797   0.02288   0.01461  -0.0057   0.7508   0.8975
   2.250   0.3060   0.02285   0.01462  -0.0055   0.7464   0.8988
   2.750   0.3544   0.02298   0.01485  -0.0050   0.7347   0.9015
   3.000   0.3820   0.02282   0.01474  -0.0049   0.7300   0.9023
   3.250   0.4056   0.02284   0.01484  -0.0045   0.7224   0.9035
   3.500   0.4323   0.02261   0.01468  -0.0041   0.7154   0.9048
   3.750   0.4569   0.02245   0.01459  -0.0036   0.7065   0.9063
   4.000   0.4857   0.02189   0.01411  -0.0030   0.6984   0.9071
   4.250   0.5100   0.02154   0.01386  -0.0023   0.6857   0.9082
   4.500   0.5356   0.02104   0.01346  -0.0015   0.6721   0.9091
   4.750   0.5613   0.02054   0.01307  -0.0008   0.6569   0.9101
   5.000   0.5867   0.02006   0.01273  -0.0001   0.6389   0.9114
   5.250   0.6083   0.01992   0.01273   0.0007   0.6124   0.9132
   5.500   0.6334   0.01941   0.01229   0.0016   0.5766   0.9146
   5.750   0.6655   0.01824   0.01084   0.0031   0.5079   0.9151
   6.000   0.6851   0.01833   0.01031   0.0052   0.4120   0.9163
   6.250   0.6970   0.01930   0.01078   0.0071   0.3254   0.9183
   6.500   0.7090   0.02037   0.01143   0.0085   0.2527   0.9205
   6.750   0.7223   0.02142   0.01213   0.0097   0.1940   0.9232
   7.000   0.7377   0.02238   0.01286   0.0106   0.1527   0.9257
   7.250   0.7543   0.02328   0.01361   0.0114   0.1251   0.9280
   7.500   0.7706   0.02420   0.01442   0.0122   0.1075   0.9305
   7.750   0.7867   0.02506   0.01528   0.0131   0.0951   0.9335
   8.000   0.8037   0.02593   0.01620   0.0137   0.0855   0.9369
   8.250   0.8197   0.02696   0.01721   0.0144   0.0788   0.9407
   8.500   0.8380   0.02791   0.01826   0.0148   0.0734   0.9451
   8.750   0.8551   0.02901   0.01937   0.0152   0.0693   0.9509
   9.000   0.8742   0.03009   0.02055   0.0155   0.0655   0.9577
   9.250   0.8947   0.03111   0.02167   0.0155   0.0616   0.9676
   9.750   0.9327   0.03349   0.02403   0.0159   0.0564   1.0000
  10.000   0.9555   0.03469   0.02543   0.0160   0.0546   1.0000
  10.250   0.9781   0.03601   0.02691   0.0162   0.0526   1.0000
  10.500   0.9986   0.03737   0.02840   0.0163   0.0506   1.0000
  10.750   1.0171   0.03874   0.02986   0.0164   0.0487   1.0000
  11.000   1.0359   0.04025   0.03141   0.0165   0.0471   1.0000
  11.250   1.0573   0.04225   0.03350   0.0165   0.0459   1.0000
  11.500   1.0727   0.04427   0.03583   0.0170   0.0451   1.0000
  11.750   1.0846   0.04655   0.03841   0.0176   0.0442   1.0000
  12.000   1.0922   0.04898   0.04114   0.0184   0.0433   1.0000
  12.250   1.0959   0.05151   0.04395   0.0192   0.0424   1.0000
  12.500   1.0972   0.05411   0.04681   0.0199   0.0415   1.0000
  12.750   1.0960   0.05684   0.04979   0.0206   0.0407   1.0000
  13.000   1.0927   0.05975   0.05291   0.0212   0.0400   1.0000
  13.250   1.0871   0.06294   0.05631   0.0215   0.0395   1.0000
  13.500   1.0781   0.06659   0.06018   0.0216   0.0392   1.0000
  13.750   1.0659   0.07069   0.06451   0.0214   0.0390   1.0000
  14.000   1.0497   0.07540   0.06945   0.0207   0.0388   1.0000
  14.250   1.0286   0.08098   0.07526   0.0191   0.0387   1.0000
  14.500   0.9998   0.08810   0.08265   0.0162   0.0388   1.0000
  14.750   0.9528   0.09943   0.09430   0.0098   0.0392   1.0000
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