Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: CLARK YM-15 AIRFOIL (clarym15-il)
Reynolds number: 500,000
Max Cl/Cd: 84.39 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarym15-il-500000-n5.txt
Download as CSV file: xf-clarym15-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK YM-15 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.7827   0.09164   0.08832  -0.0600   1.0000   0.0259
 -16.250  -0.8386   0.07833   0.07477  -0.0686   1.0000   0.0259
 -16.000  -0.8735   0.06885   0.06511  -0.0750   1.0000   0.0260
 -15.750  -0.8989   0.06092   0.05701  -0.0807   1.0000   0.0260
 -15.500  -0.9171   0.05414   0.05005  -0.0859   1.0000   0.0261
 -15.250  -0.9296   0.04844   0.04417  -0.0905   1.0000   0.0262
 -15.000  -0.9380   0.04379   0.03936  -0.0941   1.0000   0.0262
 -14.750  -0.9437   0.04009   0.03550  -0.0965   1.0000   0.0263
 -14.500  -0.9506   0.03697   0.03227  -0.0974   1.0000   0.0264
 -14.250  -0.9576   0.03459   0.02980  -0.0968   1.0000   0.0266
 -14.000  -0.9672   0.03284   0.02798  -0.0944   1.0000   0.0267
 -13.750  -0.9774   0.03152   0.02658  -0.0909   0.9994   0.0268
 -13.500  -0.9612   0.02995   0.02492  -0.0919   0.9952   0.0270
 -13.250  -0.9429   0.02866   0.02356  -0.0926   0.9909   0.0273
 -13.000  -0.9219   0.02751   0.02233  -0.0932   0.9863   0.0275
 -12.750  -0.8975   0.02643   0.02117  -0.0943   0.9832   0.0279
 -12.500  -0.8758   0.02545   0.02010  -0.0946   0.9785   0.0282
 -12.250  -0.8532   0.02448   0.01904  -0.0949   0.9735   0.0284
 -12.000  -0.8281   0.02353   0.01799  -0.0955   0.9700   0.0287
 -11.750  -0.8076   0.02271   0.01707  -0.0950   0.9633   0.0290
 -11.500  -0.7838   0.02189   0.01616  -0.0951   0.9581   0.0293
 -11.250  -0.7611   0.02115   0.01533  -0.0948   0.9524   0.0296
 -11.000  -0.7390   0.02047   0.01455  -0.0943   0.9455   0.0299
 -10.750  -0.7146   0.01983   0.01381  -0.0941   0.9403   0.0302
 -10.500  -0.6928   0.01930   0.01319  -0.0933   0.9324   0.0304
 -10.250  -0.6705   0.01858   0.01240  -0.0927   0.9257   0.0308
 -10.000  -0.6489   0.01791   0.01169  -0.0919   0.9181   0.0312
  -9.750  -0.6260   0.01733   0.01106  -0.0913   0.9107   0.0315
  -9.500  -0.6026   0.01682   0.01049  -0.0907   0.9034   0.0319
  -9.250  -0.5788   0.01635   0.00996  -0.0901   0.8953   0.0322
  -9.000  -0.5544   0.01591   0.00945  -0.0895   0.8878   0.0326
  -8.750  -0.5300   0.01548   0.00897  -0.0890   0.8794   0.0331
  -8.500  -0.5052   0.01509   0.00849  -0.0885   0.8718   0.0335
  -8.250  -0.4802   0.01471   0.00805  -0.0880   0.8633   0.0340
  -8.000  -0.4548   0.01436   0.00761  -0.0876   0.8558   0.0344
  -7.750  -0.4293   0.01403   0.00722  -0.0872   0.8476   0.0349
  -7.500  -0.4037   0.01370   0.00682  -0.0868   0.8402   0.0354
  -7.250  -0.3784   0.01332   0.00641  -0.0864   0.8326   0.0363
  -7.000  -0.3525   0.01302   0.00607  -0.0860   0.8251   0.0371
  -6.750  -0.3262   0.01274   0.00575  -0.0857   0.8181   0.0380
  -6.500  -0.2998   0.01249   0.00544  -0.0854   0.8108   0.0389
  -6.250  -0.2732   0.01226   0.00515  -0.0851   0.8041   0.0399
  -6.000  -0.2466   0.01201   0.00487  -0.0848   0.7967   0.0411
  -5.750  -0.2201   0.01178   0.00460  -0.0845   0.7893   0.0429
  -5.500  -0.1934   0.01157   0.00437  -0.0842   0.7813   0.0452
  -5.250  -0.1669   0.01137   0.00414  -0.0839   0.7723   0.0483
  -5.000  -0.1401   0.01118   0.00393  -0.0836   0.7632   0.0532
  -4.750  -0.1135   0.01101   0.00375  -0.0833   0.7543   0.0604
  -4.500  -0.0865   0.01084   0.00360  -0.0831   0.7461   0.0683
  -4.250  -0.0596   0.01070   0.00344  -0.0828   0.7378   0.0757
  -4.000  -0.0325   0.01056   0.00330  -0.0826   0.7288   0.0817
  -3.750  -0.0056   0.01046   0.00316  -0.0823   0.7194   0.0877
  -3.500   0.0216   0.01033   0.00303  -0.0821   0.7112   0.0938
  -3.250   0.0487   0.01024   0.00291  -0.0819   0.7028   0.1004
  -3.000   0.0756   0.01012   0.00279  -0.0816   0.6930   0.1087
  -2.750   0.1022   0.01001   0.00268  -0.0813   0.6823   0.1200
  -2.500   0.1286   0.00986   0.00258  -0.0810   0.6712   0.1410
  -2.250   0.1547   0.00969   0.00250  -0.0807   0.6601   0.1738
  -2.000   0.1809   0.00957   0.00244  -0.0803   0.6499   0.2032
  -1.750   0.2079   0.00948   0.00240  -0.0801   0.6405   0.2273
  -1.500   0.2345   0.00941   0.00236  -0.0798   0.6311   0.2496
  -1.250   0.2613   0.00934   0.00233  -0.0796   0.6204   0.2703
  -1.000   0.2880   0.00930   0.00230  -0.0793   0.6095   0.2901
  -0.750   0.3143   0.00928   0.00228  -0.0789   0.5979   0.3092
  -0.500   0.3410   0.00925   0.00227  -0.0786   0.5863   0.3299
  -0.250   0.3674   0.00921   0.00226  -0.0783   0.5756   0.3553
   0.250   0.4179   0.00895   0.00229  -0.0774   0.5526   0.4691
   0.500   0.4424   0.00880   0.00233  -0.0767   0.5412   0.5402
   0.750   0.4655   0.00861   0.00240  -0.0758   0.5290   0.6332
   1.000   0.4883   0.00845   0.00248  -0.0746   0.5157   0.7214
   1.250   0.5118   0.00841   0.00258  -0.0736   0.5012   0.7791
   1.500   0.5356   0.00845   0.00269  -0.0725   0.4858   0.8252
   1.750   0.5596   0.00853   0.00281  -0.0715   0.4698   0.8663
   2.000   0.5847   0.00868   0.00294  -0.0707   0.4526   0.8981
   2.250   0.6112   0.00888   0.00307  -0.0703   0.4334   0.9221
   2.500   0.6399   0.00912   0.00322  -0.0705   0.4129   0.9421
   2.750   0.6702   0.00938   0.00337  -0.0711   0.3936   0.9575
   3.000   0.7009   0.00964   0.00353  -0.0718   0.3770   0.9696
   3.250   0.7340   0.00991   0.00371  -0.0731   0.3628   0.9804
   3.500   0.7723   0.01016   0.00389  -0.0754   0.3515   0.9899
   3.750   0.8125   0.01042   0.00408  -0.0783   0.3427   0.9968
   4.000   0.8444   0.01061   0.00423  -0.0793   0.3363   1.0000
   4.250   0.8638   0.01079   0.00437  -0.0777   0.3307   1.0000
   4.500   0.8833   0.01098   0.00453  -0.0761   0.3257   1.0000
   4.750   0.9040   0.01113   0.00467  -0.0747   0.3210   1.0000
   5.000   0.9241   0.01132   0.00483  -0.0732   0.3155   1.0000
   5.250   0.9436   0.01157   0.00502  -0.0716   0.3089   1.0000
   5.500   0.9656   0.01173   0.00518  -0.0706   0.3025   1.0000
   5.750   0.9860   0.01198   0.00538  -0.0692   0.2950   1.0000
   6.000   1.0079   0.01219   0.00558  -0.0682   0.2897   1.0000
   6.250   1.0306   0.01237   0.00576  -0.0673   0.2853   1.0000
   6.500   1.0526   0.01259   0.00597  -0.0663   0.2807   1.0000
   6.750   1.0736   0.01285   0.00621  -0.0651   0.2762   1.0000
   7.000   1.0957   0.01304   0.00642  -0.0641   0.2728   1.0000
   7.250   1.1173   0.01324   0.00664  -0.0631   0.2688   1.0000
   7.500   1.1379   0.01349   0.00689  -0.0618   0.2639   1.0000
   7.750   1.1575   0.01379   0.00718  -0.0605   0.2588   1.0000
   8.000   1.1795   0.01401   0.00743  -0.0596   0.2538   1.0000
   8.250   1.2002   0.01430   0.00772  -0.0585   0.2480   1.0000
   8.500   1.2198   0.01464   0.00805  -0.0573   0.2423   1.0000
   8.750   1.2407   0.01494   0.00837  -0.0563   0.2350   1.0000
   9.000   1.2593   0.01534   0.00875  -0.0550   0.2266   1.0000
   9.250   1.2784   0.01575   0.00914  -0.0538   0.2164   1.0000
   9.500   1.2961   0.01622   0.00960  -0.0525   0.2055   1.0000
   9.750   1.3123   0.01680   0.01012  -0.0510   0.1925   1.0000
  10.000   1.3264   0.01750   0.01075  -0.0493   0.1777   1.0000
  10.250   1.3387   0.01834   0.01151  -0.0475   0.1623   1.0000
  10.500   1.3502   0.01924   0.01234  -0.0456   0.1480   1.0000
  10.750   1.3618   0.02017   0.01321  -0.0439   0.1357   1.0000
  11.000   1.3735   0.02111   0.01412  -0.0422   0.1260   1.0000
  11.250   1.3855   0.02207   0.01506  -0.0407   0.1177   1.0000
  11.500   1.3986   0.02297   0.01597  -0.0393   0.1117   1.0000
  11.750   1.4101   0.02400   0.01699  -0.0379   0.1059   1.0000
  12.000   1.4223   0.02501   0.01802  -0.0366   0.1015   1.0000
  12.250   1.4343   0.02605   0.01910  -0.0354   0.0972   1.0000
  12.500   1.4437   0.02731   0.02036  -0.0341   0.0927   1.0000
  12.750   1.4551   0.02845   0.02153  -0.0330   0.0892   1.0000
  13.000   1.4652   0.02971   0.02283  -0.0318   0.0859   1.0000
  13.250   1.4738   0.03113   0.02427  -0.0307   0.0829   1.0000
  13.500   1.4827   0.03254   0.02573  -0.0297   0.0805   1.0000
  13.750   1.4925   0.03391   0.02717  -0.0288   0.0785   1.0000
  14.000   1.5007   0.03545   0.02876  -0.0279   0.0762   1.0000
  14.250   1.5071   0.03719   0.03055  -0.0270   0.0738   1.0000
  14.500   1.5119   0.03913   0.03252  -0.0262   0.0714   1.0000
  14.750   1.5197   0.04082   0.03429  -0.0255   0.0691   1.0000
  15.000   1.5254   0.04278   0.03631  -0.0249   0.0667   1.0000
  15.250   1.5287   0.04501   0.03859  -0.0243   0.0643   1.0000
  15.500   1.5313   0.04739   0.04102  -0.0239   0.0621   1.0000
  15.750   1.5355   0.04963   0.04334  -0.0235   0.0598   1.0000
  16.000   1.5371   0.05220   0.04597  -0.0233   0.0571   1.0000
  16.250   1.5359   0.05517   0.04900  -0.0231   0.0544   1.0000
  16.500   1.5359   0.05806   0.05195  -0.0231   0.0511   1.0000
  16.750   1.5312   0.06155   0.05549  -0.0232   0.0475   1.0000
  17.000   1.5271   0.06505   0.05905  -0.0234   0.0435   1.0000
  17.250   1.5187   0.06917   0.06321  -0.0238   0.0390   1.0000
  17.500   1.5066   0.07386   0.06794  -0.0244   0.0333   1.0000
  17.750   1.4877   0.07954   0.07365  -0.0254   0.0264   1.0000
  18.000   1.4671   0.08562   0.07978  -0.0267   0.0215   1.0000
<< Back to CLARK YM-15 AIRFOIL (clarym15-il)

Polar data table (+)

Polar graphs


<< Back to CLARK YM-15 AIRFOIL (clarym15-il)