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HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il)
Reynolds number: 500,000
Max Cl/Cd: 70.42 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hsnlf213-il-500000.txt
Download as CSV file: xf-hsnlf213-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.8156   0.05053   0.04688  -0.0290   0.8075   0.0136
 -10.250  -0.8364   0.04614   0.04216  -0.0260   0.8055   0.0136
 -10.000  -0.8492   0.04130   0.03693  -0.0234   0.8037   0.0137
  -9.750  -0.8418   0.03906   0.03455  -0.0223   0.8021   0.0140
  -9.500  -0.7666   0.05015   0.04650  -0.0265   0.8002   0.0161
  -9.250  -0.7862   0.04243   0.03827  -0.0235   0.7982   0.0153
  -9.000  -0.7910   0.03622   0.03148  -0.0207   0.7964   0.0154
  -8.750  -0.7821   0.03239   0.02716  -0.0189   0.7948   0.0162
  -8.500  -0.7673   0.02965   0.02393  -0.0173   0.7933   0.0168
  -8.250  -0.7513   0.02668   0.02051  -0.0161   0.7919   0.0174
  -8.000  -0.7291   0.02551   0.01930  -0.0160   0.7906   0.0182
  -7.750  -0.7051   0.02485   0.01859  -0.0158   0.7892   0.0189
  -7.500  -0.6813   0.02327   0.01680  -0.0154   0.7880   0.0194
  -7.250  -0.6564   0.02179   0.01514  -0.0151   0.7867   0.0199
  -7.000  -0.6308   0.02058   0.01377  -0.0148   0.7851   0.0204
  -6.750  -0.6049   0.01963   0.01268  -0.0146   0.7835   0.0210
  -6.500  -0.5785   0.01901   0.01194  -0.0144   0.7820   0.0215
  -6.250  -0.5549   0.01744   0.01036  -0.0140   0.7807   0.0226
  -6.000  -0.5293   0.01690   0.00982  -0.0139   0.7794   0.0238
  -5.750  -0.5037   0.01634   0.00922  -0.0137   0.7781   0.0250
  -5.500  -0.4781   0.01580   0.00862  -0.0134   0.7769   0.0262
  -5.250  -0.4542   0.01504   0.00781  -0.0129   0.7757   0.0275
  -5.000  -0.4297   0.01450   0.00727  -0.0126   0.7744   0.0295
  -4.750  -0.4036   0.01416   0.00691  -0.0125   0.7730   0.0318
  -4.500  -0.3778   0.01368   0.00641  -0.0124   0.7718   0.0347
  -4.250  -0.3511   0.01333   0.00609  -0.0124   0.7705   0.0386
  -4.000  -0.3245   0.01296   0.00572  -0.0124   0.7691   0.0433
  -3.750  -0.2974   0.01269   0.00546  -0.0125   0.7676   0.0505
  -3.500  -0.2715   0.01222   0.00511  -0.0125   0.7660   0.0719
  -3.250  -0.2480   0.01142   0.00477  -0.0123   0.7645   0.1687
  -3.000  -0.2293   0.00996   0.00430  -0.0118   0.7631   0.4096
  -2.750  -0.2124   0.00918   0.00478  -0.0098   0.7618   0.7112
  -2.500  -0.1829   0.00954   0.00498  -0.0100   0.7605   0.7417
  -2.250  -0.1546   0.00986   0.00526  -0.0098   0.7592   0.7544
  -2.000  -0.1269   0.01016   0.00555  -0.0095   0.7580   0.7644
  -1.750  -0.0989   0.01040   0.00581  -0.0093   0.7567   0.7756
  -1.500  -0.0727   0.01075   0.00623  -0.0083   0.7550   0.7906
  -1.250  -0.0475   0.01108   0.00661  -0.0071   0.7532   0.8052
  -1.000  -0.0227   0.01138   0.00695  -0.0057   0.7514   0.8188
  -0.750   0.0036   0.01147   0.00706  -0.0051   0.7496   0.8244
  -0.500   0.0325   0.01146   0.00701  -0.0054   0.7478   0.8271
  -0.250   0.0617   0.01145   0.00696  -0.0058   0.7462   0.8296
   0.000   0.0914   0.01147   0.00692  -0.0064   0.7445   0.8316
   0.250   0.1196   0.01142   0.00683  -0.0066   0.7427   0.8328
   0.500   0.1487   0.01130   0.00674  -0.0072   0.7396   0.8337
   0.750   0.1778   0.01121   0.00665  -0.0076   0.7363   0.8346
   1.000   0.2068   0.01110   0.00653  -0.0079   0.7332   0.8354
   1.250   0.2360   0.01099   0.00639  -0.0083   0.7307   0.8359
   1.500   0.2651   0.01090   0.00626  -0.0086   0.7282   0.8364
   1.750   0.2944   0.01081   0.00620  -0.0091   0.7238   0.8371
   2.000   0.3237   0.01065   0.00604  -0.0094   0.7189   0.8377
   2.250   0.3531   0.01043   0.00580  -0.0097   0.7147   0.8380
   2.500   0.3824   0.01024   0.00560  -0.0100   0.7089   0.8383
   2.750   0.4118   0.00999   0.00535  -0.0103   0.7017   0.8386
   3.000   0.4411   0.00979   0.00511  -0.0105   0.6966   0.8391
   3.250   0.4704   0.00961   0.00500  -0.0110   0.6885   0.8396
   3.500   0.4998   0.00937   0.00473  -0.0112   0.6797   0.8399
   3.750   0.5292   0.00920   0.00461  -0.0117   0.6698   0.8401
   4.000   0.5587   0.00907   0.00452  -0.0121   0.6589   0.8403
   4.250   0.5879   0.00891   0.00437  -0.0124   0.6406   0.8404
   4.500   0.6164   0.00882   0.00421  -0.0126   0.6077   0.8406
   4.750   0.6415   0.00911   0.00417  -0.0124   0.5275   0.8410
   5.000   0.6627   0.01003   0.00458  -0.0120   0.4239   0.8415
   5.250   0.6842   0.01093   0.00507  -0.0118   0.3345   0.8418
   5.500   0.7057   0.01178   0.00554  -0.0116   0.2560   0.8420
   5.750   0.7275   0.01257   0.00600  -0.0114   0.1913   0.8421
   6.000   0.7496   0.01328   0.00644  -0.0113   0.1410   0.8423
   6.250   0.7722   0.01392   0.00689  -0.0111   0.1060   0.8424
   6.500   0.7950   0.01451   0.00734  -0.0109   0.0827   0.8425
   6.750   0.8175   0.01510   0.00784  -0.0107   0.0680   0.8428
   7.000   0.8412   0.01555   0.00828  -0.0105   0.0604   0.8432
   7.250   0.8634   0.01613   0.00886  -0.0102   0.0545   0.8435
   7.500   0.8864   0.01660   0.00934  -0.0099   0.0505   0.8436
   7.750   0.9046   0.01747   0.01020  -0.0092   0.0462   0.8437
   8.000   0.9272   0.01791   0.01070  -0.0089   0.0447   0.8438
   8.250   0.9483   0.01846   0.01130  -0.0084   0.0430   0.8439
   8.500   0.9681   0.01906   0.01193  -0.0078   0.0414   0.8440
   8.750   0.9846   0.01972   0.01263  -0.0068   0.0400   0.8442
   9.000   0.9992   0.02074   0.01366  -0.0058   0.0384   0.8446
   9.250   1.0131   0.02194   0.01494  -0.0047   0.0371   0.8450
   9.500   1.0329   0.02259   0.01564  -0.0043   0.0364   0.8452
   9.750   1.0513   0.02337   0.01649  -0.0037   0.0355   0.8454
  10.000   1.0691   0.02421   0.01740  -0.0031   0.0347   0.8455
  10.250   1.0865   0.02508   0.01832  -0.0024   0.0338   0.8457
  10.500   1.1036   0.02597   0.01928  -0.0017   0.0331   0.8459
  10.750   1.1201   0.02691   0.02026  -0.0010   0.0323   0.8461
  11.000   1.1359   0.02792   0.02130  -0.0003   0.0316   0.8463
  11.250   1.1506   0.02929   0.02271   0.0008   0.0306   0.8465
  11.500   1.1667   0.03093   0.02446   0.0019   0.0298   0.8467
  11.750   1.1820   0.03195   0.02560   0.0026   0.0295   0.8470
  12.000   1.1968   0.03309   0.02686   0.0034   0.0291   0.8473
  12.250   1.2105   0.03434   0.02824   0.0042   0.0286   0.8477
  12.500   1.2233   0.03570   0.02973   0.0051   0.0281   0.8481
  12.750   1.2348   0.03717   0.03132   0.0060   0.0276   0.8485
  13.000   1.2450   0.03869   0.03297   0.0068   0.0271   0.8490
  13.250   1.2536   0.04025   0.03466   0.0077   0.0266   0.8495
  13.500   1.2610   0.04185   0.03637   0.0085   0.0262   0.8500
  13.750   1.2677   0.04352   0.03813   0.0092   0.0257   0.8506
  14.000   1.2734   0.04534   0.04005   0.0099   0.0254   0.8512
  14.250   1.2777   0.04740   0.04222   0.0107   0.0250   0.8519
  14.500   1.2795   0.04988   0.04482   0.0115   0.0247   0.8528
  14.750   1.2751   0.05323   0.04834   0.0125   0.0243   0.8536
  15.000   1.2597   0.05799   0.05337   0.0134   0.0241   0.8542
  15.250   1.2415   0.06277   0.05840   0.0137   0.0239   0.8548
  15.500   1.2308   0.06646   0.06227   0.0134   0.0238   0.8555
  15.750   1.2178   0.07066   0.06667   0.0127   0.0237   0.8563
  16.000   1.2013   0.07578   0.07199   0.0114   0.0237   0.8570
  16.250   1.1834   0.08157   0.07798   0.0092   0.0236   0.8578
  16.500   1.1617   0.08845   0.08507   0.0061   0.0236   0.8586
  16.750   1.1356   0.09675   0.09357   0.0018   0.0236   0.8593
  17.000   1.1010   0.10739   0.10443  -0.0042   0.0237   0.8598
  17.250   1.0544   0.12167   0.11893  -0.0129   0.0239   0.8600
  17.500   1.0228   0.13430   0.13174  -0.0212   0.0241   0.8604
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