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CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: CLARK V AIRFOIL (clarkv-il)
Reynolds number: 200,000
Max Cl/Cd: 80.92 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkv-il-200000.txt
Download as CSV file: xf-clarkv-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK V 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4209   0.10285   0.09931  -0.0364   1.0000   0.0658
  -9.250  -0.4407   0.09970   0.09625  -0.0374   1.0000   0.0680
  -9.000  -0.4730   0.09659   0.09325  -0.0389   1.0000   0.0690
  -8.750  -0.4065   0.08861   0.08557  -0.0327   1.0000   0.0713
  -8.500  -0.4046   0.08678   0.08375  -0.0302   1.0000   0.0723
  -8.250  -0.4041   0.08417   0.08117  -0.0294   0.9994   0.0739
  -8.000  -0.3989   0.07960   0.07659  -0.0326   0.9965   0.0769
  -7.750  -0.5563   0.07808   0.07494  -0.0369   0.9995   0.0712
  -7.500  -0.5350   0.07618   0.07303  -0.0368   0.9969   0.0729
  -7.250  -0.5147   0.07172   0.06850  -0.0418   0.9927   0.0757
  -7.000  -0.5092   0.05864   0.05471  -0.0577   0.9839   0.0838
  -6.750  -0.4095   0.04697   0.04365  -0.0607   0.9710   0.0894
  -6.500  -0.4825   0.03860   0.03294  -0.0624   0.9737   0.0582
  -6.250  -0.4507   0.03545   0.02933  -0.0646   0.9714   0.0580
  -6.000  -0.4302   0.03201   0.02549  -0.0645   0.9661   0.0583
  -5.750  -0.4007   0.02933   0.02243  -0.0656   0.9626   0.0584
  -5.500  -0.3675   0.02690   0.01972  -0.0675   0.9602   0.0596
  -5.250  -0.3305   0.02573   0.01844  -0.0698   0.9581   0.0620
  -5.000  -0.3047   0.02460   0.01713  -0.0696   0.9526   0.0632
  -4.750  -0.2719   0.02348   0.01581  -0.0707   0.9487   0.0646
  -4.500  -0.2350   0.02260   0.01474  -0.0725   0.9459   0.0670
  -4.250  -0.1953   0.02204   0.01399  -0.0748   0.9438   0.0694
  -4.000  -0.1705   0.02080   0.01274  -0.0745   0.9381   0.0718
  -3.750  -0.1374   0.02008   0.01205  -0.0757   0.9339   0.0753
  -3.500  -0.1000   0.01950   0.01144  -0.0776   0.9310   0.0804
  -3.250  -0.0607   0.01873   0.01071  -0.0800   0.9291   0.0884
  -3.000  -0.0384   0.01835   0.01032  -0.0790   0.9213   0.0973
  -2.750  -0.0029   0.01762   0.00977  -0.0807   0.9177   0.1233
  -2.500   0.0356   0.01670   0.00929  -0.0832   0.9155   0.2072
  -2.250   0.0620   0.01601   0.00923  -0.0835   0.9096   0.3573
  -2.000   0.0925   0.01548   0.00911  -0.0842   0.9045   0.4723
  -1.750   0.1268   0.01477   0.00898  -0.0853   0.9017   0.6139
  -1.500   0.1578   0.01406   0.00896  -0.0848   0.8998   0.7992
  -1.250   0.2064   0.01387   0.00894  -0.0877   0.8992   0.9338
  -1.000   0.2782   0.01379   0.00876  -0.0966   0.8996   0.9884
  -0.750   0.3144   0.01381   0.00868  -0.0986   0.8919   1.0000
  -0.500   0.3523   0.01354   0.00832  -0.1006   0.8880   1.0000
  -0.250   0.3939   0.01322   0.00791  -0.1032   0.8855   1.0000
   0.000   0.4136   0.01315   0.00778  -0.1014   0.8756   1.0000
   0.250   0.4561   0.01266   0.00722  -0.1039   0.8716   1.0000
   0.500   0.4819   0.01242   0.00692  -0.1031   0.8619   1.0000
   0.750   0.5203   0.01201   0.00646  -0.1048   0.8567   1.0000
   1.000   0.5442   0.01192   0.00632  -0.1038   0.8473   1.0000
   1.250   0.5798   0.01162   0.00599  -0.1050   0.8414   1.0000
   1.500   0.6035   0.01157   0.00590  -0.1039   0.8311   1.0000
   1.750   0.6395   0.01130   0.00559  -0.1052   0.8246   1.0000
   2.000   0.6623   0.01128   0.00555  -0.1039   0.8129   1.0000
   2.250   0.6880   0.01121   0.00546  -0.1032   0.8013   1.0000
   2.500   0.7153   0.01109   0.00530  -0.1027   0.7884   1.0000
   2.750   0.7418   0.01101   0.00518  -0.1020   0.7743   1.0000
   3.000   0.7679   0.01099   0.00511  -0.1013   0.7605   1.0000
   3.250   0.7939   0.01100   0.00509  -0.1007   0.7470   1.0000
   3.500   0.8190   0.01105   0.00510  -0.0999   0.7327   1.0000
   3.750   0.8428   0.01112   0.00516  -0.0989   0.7170   1.0000
   4.000   0.8659   0.01122   0.00523  -0.0977   0.7000   1.0000
   4.250   0.8889   0.01134   0.00533  -0.0965   0.6824   1.0000
   4.500   0.9120   0.01148   0.00544  -0.0953   0.6640   1.0000
   4.750   0.9348   0.01164   0.00555  -0.0941   0.6440   1.0000
   5.000   0.9560   0.01184   0.00569  -0.0926   0.6215   1.0000
   5.250   0.9767   0.01207   0.00585  -0.0910   0.5965   1.0000
   5.500   0.9953   0.01235   0.00604  -0.0890   0.5674   1.0000
   5.750   1.0132   0.01268   0.00626  -0.0869   0.5366   1.0000
   6.000   1.0307   0.01305   0.00653  -0.0848   0.5055   1.0000
   6.250   1.0472   0.01348   0.00685  -0.0826   0.4736   1.0000
   6.500   1.0628   0.01397   0.00720  -0.0802   0.4408   1.0000
   6.750   1.0776   0.01451   0.00761  -0.0778   0.4081   1.0000
   7.000   1.0920   0.01510   0.00806  -0.0754   0.3780   1.0000
   7.250   1.1063   0.01573   0.00858  -0.0730   0.3509   1.0000
   7.500   1.1209   0.01635   0.00911  -0.0707   0.3250   1.0000
   7.750   1.1336   0.01700   0.00965  -0.0681   0.3004   1.0000
   8.000   1.1456   0.01765   0.01020  -0.0655   0.2756   1.0000
   8.250   1.1585   0.01828   0.01076  -0.0631   0.2507   1.0000
   8.500   1.1709   0.01899   0.01138  -0.0607   0.2294   1.0000
   8.750   1.1851   0.01966   0.01202  -0.0586   0.2105   1.0000
   9.000   1.1988   0.02037   0.01271  -0.0566   0.1923   1.0000
   9.250   1.2118   0.02115   0.01345  -0.0545   0.1748   1.0000
   9.500   1.2239   0.02199   0.01425  -0.0524   0.1579   1.0000
   9.750   1.2364   0.02284   0.01510  -0.0504   0.1393   1.0000
  10.000   1.2475   0.02381   0.01600  -0.0482   0.1165   1.0000
  10.250   1.2531   0.02521   0.01722  -0.0456   0.0896   1.0000
  10.500   1.2532   0.02710   0.01894  -0.0423   0.0664   1.0000
  10.750   1.2542   0.02895   0.02073  -0.0392   0.0545   1.0000
  11.000   1.2599   0.03049   0.02232  -0.0368   0.0480   1.0000
  11.250   1.2621   0.03233   0.02421  -0.0342   0.0441   1.0000
  11.500   1.2682   0.03392   0.02587  -0.0322   0.0408   1.0000
  11.750   1.2700   0.03589   0.02787  -0.0300   0.0387   1.0000
  12.000   1.2710   0.03807   0.03009  -0.0277   0.0371   1.0000
  12.250   1.2775   0.03983   0.03200  -0.0260   0.0357   1.0000
  12.500   1.2834   0.04169   0.03395  -0.0244   0.0342   1.0000
  12.750   1.2888   0.04361   0.03593  -0.0229   0.0328   1.0000
  13.000   1.2932   0.04569   0.03804  -0.0214   0.0316   1.0000
  13.250   1.2998   0.04793   0.04032  -0.0197   0.0304   1.0000
  13.500   1.3067   0.04993   0.04249  -0.0185   0.0296   1.0000
  13.750   1.3134   0.05205   0.04477  -0.0172   0.0289   1.0000
  14.000   1.3196   0.05428   0.04716  -0.0160   0.0282   1.0000
  14.250   1.3247   0.05668   0.04970  -0.0148   0.0276   1.0000
  14.500   1.3283   0.05924   0.05242  -0.0138   0.0271   1.0000
  14.750   1.3300   0.06195   0.05528  -0.0129   0.0266   1.0000
  15.000   1.3308   0.06478   0.05825  -0.0122   0.0261   1.0000
  15.250   1.3326   0.06770   0.06126  -0.0115   0.0256   1.0000
  15.500   1.3334   0.07129   0.06498  -0.0107   0.0250   1.0000
  15.750   1.3228   0.07579   0.06970  -0.0104   0.0248   1.0000
  16.000   1.3090   0.08026   0.07443  -0.0109   0.0247   1.0000
  16.250   1.2942   0.08520   0.07961  -0.0119   0.0246   1.0000
  16.500   1.2784   0.09058   0.08523  -0.0134   0.0245   1.0000
  16.750   1.2616   0.09645   0.09133  -0.0154   0.0245   1.0000
  17.000   1.2437   0.10282   0.09792  -0.0181   0.0245   1.0000
  17.250   1.2252   0.10967   0.10498  -0.0214   0.0246   1.0000
  17.500   1.2059   0.11701   0.11252  -0.0252   0.0246   1.0000
  17.750   1.1861   0.12487   0.12057  -0.0297   0.0247   1.0000
  18.000   1.1665   0.13318   0.12906  -0.0348   0.0249   1.0000
  18.250   1.1427   0.14352   0.13965  -0.0426   0.0252   1.0000
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