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WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il)
Reynolds number: 200,000
Max Cl/Cd: 66.25 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx05h126-il-200000.txt
Download as CSV file: xf-fx05h126-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 05-H-126 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3905   0.09868   0.09484  -0.0115   0.6662   0.0438
  -8.250  -0.3988   0.09485   0.09104  -0.0173   0.6653   0.0440
  -8.000  -0.4046   0.09109   0.08722  -0.0216   0.6645   0.0441
  -7.750  -0.3937   0.08578   0.08198  -0.0189   0.6637   0.0451
  -7.500  -0.3814   0.08322   0.07942  -0.0175   0.6628   0.0462
  -7.250  -0.3734   0.08017   0.07638  -0.0191   0.6619   0.0472
  -7.000  -0.3657   0.07687   0.07307  -0.0218   0.6608   0.0488
  -6.750  -0.3579   0.07317   0.06934  -0.0254   0.6597   0.0514
  -6.500  -0.3521   0.06998   0.06567  -0.0324   0.6585   0.0549
  -6.250  -0.3443   0.06354   0.05923  -0.0339   0.6571   0.0560
  -6.000  -0.3283   0.06043   0.05621  -0.0342   0.6556   0.0573
  -5.750  -0.3118   0.05793   0.05368  -0.0347   0.6544   0.0589
  -5.500  -0.2946   0.05530   0.05094  -0.0354   0.6533   0.0616
  -5.250  -0.2718   0.05545   0.05031  -0.0358   0.6522   0.0680
  -5.000  -0.2599   0.04873   0.04371  -0.0368   0.6513   0.0700
  -4.750  -0.2403   0.04643   0.04140  -0.0370   0.6504   0.0722
  -4.500  -0.2197   0.04448   0.03932  -0.0369   0.6495   0.0760
  -4.250  -0.1999   0.04223   0.03654  -0.0363   0.6486   0.0844
  -4.000  -0.1794   0.04028   0.03464  -0.0361   0.6477   0.0882
  -3.750  -0.1550   0.03885   0.03289  -0.0367   0.6458   0.0998
  -3.500  -0.1296   0.03728   0.03138  -0.0377   0.6442   0.1043
  -3.250  -0.1053   0.03607   0.02998  -0.0383   0.6427   0.1167
  -3.000  -0.0688   0.03100   0.02360  -0.0355   0.6414   0.0541
  -2.750  -0.0426   0.02908   0.02148  -0.0355   0.6396   0.0516
  -2.500  -0.0157   0.02808   0.02026  -0.0353   0.6379   0.0516
  -2.250   0.0114   0.02740   0.01940  -0.0352   0.6367   0.0525
  -2.000   0.0384   0.02661   0.01847  -0.0350   0.6355   0.0522
  -1.750   0.0645   0.02592   0.01767  -0.0343   0.6343   0.0526
  -1.500   0.0897   0.02536   0.01701  -0.0334   0.6332   0.0537
  -1.250   0.1160   0.02539   0.01702  -0.0337   0.6312   0.0550
  -1.000   0.1417   0.02575   0.01758  -0.0359   0.6267   0.0592
  -0.750   0.1661   0.02591   0.01776  -0.0360   0.6240   0.0649
  -0.500   0.1893   0.02572   0.01755  -0.0353   0.6219   0.0717
  -0.250   0.2110   0.02520   0.01722  -0.0339   0.6203   0.1191
   0.000   0.3565   0.02213   0.01662  -0.0559   0.6195   1.0000
   0.250   0.3778   0.02223   0.01657  -0.0544   0.6182   1.0000
   0.500   0.3990   0.02239   0.01659  -0.0528   0.6172   1.0000
   0.750   0.4270   0.02464   0.01895  -0.0577   0.6092   1.0000
   1.000   0.4492   0.02501   0.01924  -0.0570   0.6067   1.0000
   1.250   0.4713   0.02521   0.01936  -0.0558   0.6051   1.0000
   1.500   0.4935   0.02528   0.01934  -0.0544   0.6037   1.0000
   1.750   0.5159   0.02530   0.01926  -0.0528   0.6026   1.0000
   2.000   0.5339   0.02783   0.02189  -0.0560   0.5929   1.0000
   2.250   0.5562   0.02806   0.02208  -0.0549   0.5907   1.0000
   2.500   0.5795   0.02803   0.02199  -0.0535   0.5892   1.0000
   2.750   0.6033   0.02790   0.02180  -0.0519   0.5880   1.0000
   3.000   0.6275   0.02773   0.02157  -0.0503   0.5871   1.0000
   3.250   0.6377   0.03055   0.02450  -0.0526   0.5754   1.0000
   3.500   0.6625   0.03040   0.02431  -0.0512   0.5740   1.0000
   3.750   0.6881   0.03012   0.02400  -0.0498   0.5729   1.0000
   4.000   0.7138   0.02986   0.02372  -0.0483   0.5721   1.0000
   4.250   0.7199   0.03254   0.02650  -0.0496   0.5597   1.0000
   4.500   0.7465   0.03223   0.02618  -0.0483   0.5586   1.0000
   4.750   0.7500   0.03472   0.02873  -0.0487   0.5473   1.0000
   5.000   0.7763   0.03450   0.02853  -0.0476   0.5454   1.0000
   5.250   0.8043   0.03408   0.02811  -0.0465   0.5442   1.0000
   5.500   0.8325   0.03361   0.02767  -0.0453   0.5433   1.0000
   5.750   0.8615   0.03302   0.02709  -0.0441   0.5426   1.0000
   6.000   0.8910   0.03236   0.02647  -0.0429   0.5421   1.0000
   6.250   0.8623   0.03797   0.03218  -0.0440   0.5190   1.0000
   6.500   0.8953   0.03695   0.03121  -0.0430   0.5173   1.0000
   6.750   0.9380   0.03449   0.02880  -0.0416   0.5167   1.0000
   7.000   0.9819   0.03157   0.02594  -0.0398   0.5168   1.0000
   7.250   1.0248   0.02869   0.02309  -0.0383   0.5169   1.0000
   7.500   1.0614   0.02677   0.02122  -0.0371   0.5161   1.0000
   7.750   1.0983   0.02479   0.01927  -0.0360   0.5150   1.0000
   8.000   1.1353   0.02275   0.01724  -0.0350   0.5136   1.0000
   8.250   1.1530   0.02323   0.01792  -0.0347   0.5029   1.0000
   8.500   1.1897   0.02130   0.01602  -0.0338   0.5001   1.0000
   8.750   1.2094   0.02156   0.01648  -0.0336   0.4893   1.0000
   9.000   1.2337   0.02123   0.01629  -0.0332   0.4791   1.0000
   9.250   1.2576   0.02093   0.01615  -0.0328   0.4652   1.0000
   9.500   1.2827   0.02050   0.01580  -0.0324   0.4462   1.0000
   9.750   1.3091   0.01976   0.01497  -0.0315   0.4146   1.0000
  10.000   1.3193   0.02042   0.01527  -0.0299   0.3643   1.0000
  10.250   1.3031   0.02330   0.01790  -0.0278   0.3230   1.0000
  10.500   1.2811   0.02656   0.02089  -0.0252   0.2836   1.0000
  10.750   1.2581   0.03021   0.02424  -0.0231   0.2436   1.0000
  11.000   1.2364   0.03394   0.02766  -0.0212   0.2056   1.0000
  11.250   1.2180   0.03751   0.03097  -0.0197   0.1749   1.0000
  11.500   1.2054   0.04069   0.03395  -0.0184   0.1514   1.0000
  11.750   1.1992   0.04350   0.03661  -0.0175   0.1337   1.0000
  12.000   1.1977   0.04599   0.03902  -0.0167   0.1203   1.0000
  12.250   1.1983   0.04834   0.04131  -0.0161   0.1090   1.0000
  12.500   1.1999   0.05065   0.04355  -0.0156   0.1005   1.0000
  12.750   1.2030   0.05284   0.04574  -0.0151   0.0931   1.0000
  13.000   1.2069   0.05494   0.04785  -0.0146   0.0871   1.0000
  13.250   1.2117   0.05703   0.04999  -0.0142   0.0813   1.0000
  13.500   1.2150   0.05924   0.05219  -0.0137   0.0756   1.0000
  13.750   1.2203   0.06140   0.05444  -0.0136   0.0697   1.0000
  14.000   1.2224   0.06380   0.05684  -0.0132   0.0639   1.0000
  14.250   1.2253   0.06644   0.05957  -0.0133   0.0569   1.0000
  14.500   1.2260   0.06922   0.06239  -0.0132   0.0497   1.0000
  14.750   1.2228   0.07258   0.06573  -0.0133   0.0419   1.0000
  15.000   1.2234   0.07558   0.06875  -0.0134   0.0369   1.0000
  15.250   1.2239   0.07841   0.07162  -0.0132   0.0331   1.0000
  15.500   1.2258   0.08131   0.07459  -0.0135   0.0300   1.0000
  15.750   1.2260   0.08405   0.07727  -0.0132   0.0279   1.0000
  16.000   1.2312   0.08639   0.07977  -0.0129   0.0266   1.0000
  16.250   1.2353   0.08893   0.08241  -0.0128   0.0251   1.0000
  16.500   1.2395   0.09138   0.08493  -0.0128   0.0241   1.0000
  16.750   1.2433   0.09388   0.08748  -0.0127   0.0232   1.0000
  17.000   1.2498   0.09573   0.08934  -0.0119   0.0224   1.0000
  17.250   1.2528   0.09842   0.09219  -0.0116   0.0216   1.0000
  17.500   1.2546   0.10146   0.09541  -0.0118   0.0214   1.0000
  17.750   1.2515   0.10542   0.09959  -0.0128   0.0206   1.0000
  18.000   1.2486   0.10936   0.10372  -0.0137   0.0202   1.0000
  18.250   1.2445   0.11358   0.10812  -0.0149   0.0197   1.0000
  18.500   1.2395   0.11806   0.11275  -0.0166   0.0192   1.0000
  18.750   1.2328   0.12291   0.11779  -0.0183   0.0191   1.0000
  19.000   1.2235   0.12836   0.12345  -0.0205   0.0190   1.0000
  19.250   1.2131   0.13419   0.12945  -0.0232   0.0187   1.0000
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