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HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il)
Reynolds number: 200,000
Max Cl/Cd: 49.94 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hsnlf213-il-200000-n5.txt
Download as CSV file: xf-hsnlf213-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6401   0.08700   0.08328  -0.0194   0.8225   0.0152
 -10.750  -0.6871   0.07173   0.06780  -0.0300   0.8208   0.0146
 -10.500  -0.7196   0.06399   0.05981  -0.0324   0.8186   0.0144
 -10.250  -0.7403   0.05882   0.05443  -0.0327   0.8157   0.0145
 -10.000  -0.7543   0.05485   0.05023  -0.0316   0.8127   0.0147
  -9.750  -0.7639   0.05121   0.04632  -0.0298   0.8102   0.0151
  -9.500  -0.7703   0.04684   0.04155  -0.0280   0.8081   0.0156
  -9.250  -0.7741   0.04201   0.03618  -0.0258   0.8063   0.0161
  -9.000  -0.7709   0.03765   0.03123  -0.0237   0.8046   0.0164
  -8.750  -0.7603   0.03400   0.02698  -0.0221   0.8029   0.0168
  -8.500  -0.7435   0.03133   0.02385  -0.0211   0.8010   0.0172
  -8.250  -0.7228   0.02979   0.02217  -0.0208   0.7991   0.0177
  -8.000  -0.7007   0.02857   0.02081  -0.0204   0.7971   0.0182
  -7.750  -0.6778   0.02754   0.01961  -0.0201   0.7951   0.0192
  -7.500  -0.6543   0.02630   0.01813  -0.0197   0.7933   0.0203
  -7.250  -0.6298   0.02496   0.01652  -0.0192   0.7918   0.0211
  -7.000  -0.6052   0.02367   0.01508  -0.0189   0.7904   0.0218
  -6.750  -0.5811   0.02270   0.01406  -0.0186   0.7892   0.0226
  -6.500  -0.5561   0.02187   0.01319  -0.0184   0.7877   0.0236
  -6.250  -0.5309   0.02109   0.01234  -0.0183   0.7861   0.0248
  -6.000  -0.5054   0.02046   0.01161  -0.0181   0.7843   0.0266
  -5.750  -0.4817   0.01967   0.01083  -0.0178   0.7824   0.0283
  -5.500  -0.4572   0.01907   0.01021  -0.0175   0.7806   0.0300
  -5.250  -0.4328   0.01849   0.00958  -0.0172   0.7789   0.0320
  -5.000  -0.4087   0.01792   0.00899  -0.0168   0.7775   0.0348
  -4.750  -0.3838   0.01748   0.00852  -0.0166   0.7762   0.0382
  -4.500  -0.3589   0.01704   0.00802  -0.0163   0.7750   0.0417
  -4.250  -0.3341   0.01662   0.00760  -0.0160   0.7738   0.0478
  -4.000  -0.3086   0.01621   0.00722  -0.0160   0.7722   0.0566
  -3.750  -0.2828   0.01581   0.00688  -0.0160   0.7701   0.0729
  -3.500  -0.2582   0.01530   0.00656  -0.0159   0.7683   0.1091
  -3.250  -0.2363   0.01447   0.00621  -0.0156   0.7666   0.2146
  -3.000  -0.2200   0.01308   0.00576  -0.0147   0.7649   0.4257
  -2.750  -0.2072   0.01304   0.00703  -0.0102   0.7632   0.6776
  -2.500  -0.1786   0.01335   0.00711  -0.0107   0.7616   0.7407
  -2.250  -0.1536   0.01386   0.00759  -0.0093   0.7602   0.7669
  -2.000  -0.1305   0.01437   0.00811  -0.0072   0.7590   0.7897
  -1.750  -0.1078   0.01479   0.00855  -0.0049   0.7577   0.8075
  -1.500  -0.0811   0.01492   0.00864  -0.0047   0.7554   0.8169
  -1.250  -0.0535   0.01494   0.00863  -0.0047   0.7532   0.8196
  -1.000  -0.0255   0.01496   0.00860  -0.0049   0.7513   0.8222
  -0.750   0.0028   0.01494   0.00853  -0.0052   0.7493   0.8241
  -0.500   0.0313   0.01490   0.00843  -0.0056   0.7475   0.8258
  -0.250   0.0599   0.01486   0.00834  -0.0060   0.7458   0.8274
   0.000   0.0886   0.01482   0.00824  -0.0065   0.7442   0.8288
   0.250   0.1173   0.01479   0.00815  -0.0069   0.7428   0.8301
   0.500   0.1466   0.01484   0.00822  -0.0078   0.7394   0.8310
   0.750   0.1754   0.01487   0.00824  -0.0084   0.7363   0.8320
   1.000   0.2038   0.01484   0.00821  -0.0088   0.7334   0.8327
   1.250   0.2324   0.01478   0.00814  -0.0090   0.7307   0.8333
   1.500   0.2610   0.01469   0.00803  -0.0092   0.7284   0.8337
   1.750   0.2893   0.01470   0.00809  -0.0097   0.7240   0.8344
   2.000   0.3176   0.01468   0.00811  -0.0100   0.7193   0.8352
   2.250   0.3462   0.01457   0.00800  -0.0102   0.7156   0.8358
   2.500   0.3750   0.01438   0.00780  -0.0103   0.7123   0.8362
   2.750   0.4031   0.01435   0.00785  -0.0107   0.7044   0.8367
   3.000   0.4319   0.01407   0.00757  -0.0107   0.6986   0.8371
   3.250   0.4600   0.01388   0.00745  -0.0108   0.6887   0.8377
   3.500   0.4884   0.01355   0.00713  -0.0106   0.6788   0.8385
   3.750   0.5168   0.01328   0.00690  -0.0107   0.6672   0.8391
   4.000   0.5452   0.01311   0.00681  -0.0109   0.6526   0.8395
   4.250   0.5733   0.01296   0.00674  -0.0110   0.6311   0.8399
   4.500   0.6012   0.01271   0.00645  -0.0109   0.5964   0.8402
   4.750   0.6267   0.01255   0.00597  -0.0101   0.5290   0.8406
   5.000   0.6466   0.01317   0.00605  -0.0090   0.4353   0.8412
   5.250   0.6647   0.01413   0.00655  -0.0082   0.3475   0.8421
   5.500   0.6827   0.01512   0.00713  -0.0075   0.2683   0.8429
   5.750   0.7017   0.01600   0.00770  -0.0071   0.2068   0.8434
   6.000   0.7215   0.01680   0.00825  -0.0067   0.1598   0.8439
   6.250   0.7421   0.01750   0.00879  -0.0063   0.1270   0.8443
   6.500   0.7630   0.01816   0.00934  -0.0060   0.1036   0.8447
   6.750   0.7842   0.01878   0.00989  -0.0056   0.0874   0.8452
   7.000   0.8052   0.01939   0.01047  -0.0052   0.0763   0.8458
   7.250   0.8252   0.02007   0.01111  -0.0048   0.0678   0.8465
   7.750   0.8639   0.02141   0.01248  -0.0036   0.0564   0.8476
   8.000   0.8824   0.02201   0.01317  -0.0028   0.0529   0.8481
   8.250   0.8991   0.02271   0.01393  -0.0019   0.0500   0.8486
   8.500   0.9155   0.02359   0.01484  -0.0012   0.0475   0.8492
   8.750   0.9312   0.02459   0.01588  -0.0004   0.0456   0.8498
   9.000   0.9490   0.02542   0.01681   0.0002   0.0439   0.8504
   9.250   0.9663   0.02629   0.01776   0.0008   0.0421   0.8510
   9.500   0.9832   0.02718   0.01872   0.0015   0.0404   0.8517
   9.750   0.9990   0.02816   0.01975   0.0021   0.0390   0.8524
  10.000   1.0131   0.02935   0.02096   0.0030   0.0378   0.8531
  10.250   1.0286   0.03049   0.02216   0.0039   0.0369   0.8539
  10.500   1.0452   0.03151   0.02332   0.0046   0.0361   0.8547
  10.750   1.0615   0.03260   0.02454   0.0054   0.0352   0.8555
  11.000   1.0774   0.03372   0.02577   0.0061   0.0342   0.8564
  11.250   1.0925   0.03487   0.02702   0.0068   0.0332   0.8575
  11.500   1.1067   0.03606   0.02830   0.0074   0.0323   0.8588
  11.750   1.1202   0.03732   0.02964   0.0081   0.0315   0.8602
  12.000   1.1331   0.03870   0.03111   0.0088   0.0309   0.8615
  12.500   1.1575   0.04201   0.03464   0.0105   0.0298   0.8638
  12.750   1.1671   0.04374   0.03659   0.0114   0.0294   0.8653
  13.000   1.1748   0.04564   0.03872   0.0122   0.0289   0.8671
  13.250   1.1804   0.04770   0.04101   0.0131   0.0284   0.8691
  13.500   1.1839   0.04993   0.04346   0.0139   0.0278   0.8713
  13.750   1.1855   0.05232   0.04608   0.0146   0.0273   0.8741
  14.000   1.1854   0.05488   0.04885   0.0151   0.0268   0.8771
  14.250   1.1835   0.05761   0.05180   0.0156   0.0264   0.8811
  14.500   1.1795   0.06059   0.05499   0.0160   0.0261   0.8865
  15.000   1.1649   0.06735   0.06221   0.0162   0.0256   0.9084
  15.250   1.1525   0.07108   0.06618   0.0160   0.0255   1.0000
  15.500   1.1416   0.07568   0.07096   0.0147   0.0253   1.0000
  15.750   1.1285   0.08092   0.07640   0.0127   0.0251   1.0000
  16.000   1.1120   0.08706   0.08273   0.0100   0.0250   1.0000
  16.250   1.0907   0.09456   0.09046   0.0061   0.0250   1.0000
  16.500   1.0597   0.10472   0.10088   0.0001   0.0250   1.0000
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