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Dormoy (dormoy-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 100,000
Max Cl/Cd: 50.35 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dormoy-il-100000.txt
Download as CSV file: xf-dormoy-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Dormoy                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3311   0.11610   0.11149  -0.0223   1.0000   0.0738
 -11.750  -0.3382   0.11363   0.10906  -0.0247   1.0000   0.0758
 -11.500  -0.3493   0.11132   0.10682  -0.0277   1.0000   0.0766
 -11.250  -0.3280   0.10555   0.10104  -0.0250   1.0000   0.0806
 -11.000  -0.3240   0.10221   0.09773  -0.0253   1.0000   0.0853
 -10.750  -0.3305   0.09921   0.09479  -0.0273   1.0000   0.0887
 -10.500  -0.3454   0.09661   0.09227  -0.0307   1.0000   0.0899
 -10.250  -0.3226   0.09165   0.08730  -0.0274   1.0000   0.0960
 -10.000  -0.3279   0.08851   0.08422  -0.0289   1.0000   0.1009
  -9.750  -0.3468   0.08583   0.08165  -0.0324   1.0000   0.1025
  -9.500  -0.3246   0.08130   0.07711  -0.0289   1.0000   0.1098
  -9.250  -0.3372   0.07842   0.07432  -0.0308   1.0000   0.1141
  -9.000  -0.3608   0.07590   0.07194  -0.0333   1.0000   0.1151
  -8.750  -0.3362   0.07149   0.06753  -0.0295   1.0000   0.1240
  -8.500  -0.3569   0.06905   0.06522  -0.0302   1.0000   0.1268
  -8.250  -0.3826   0.06617   0.06244  -0.0336   1.0000   0.1281
  -8.000  -0.4241   0.07324   0.06918  -0.0312   1.0000   0.1237
  -7.750  -0.4373   0.06977   0.06564  -0.0366   1.0000   0.1295
  -7.500  -0.4256   0.06727   0.06327  -0.0316   1.0000   0.1381
  -7.250  -0.4297   0.06410   0.06010  -0.0319   1.0000   0.1450
  -7.000  -0.4387   0.06279   0.05854  -0.0333   1.0000   0.1560
  -6.750  -0.4302   0.05935   0.05539  -0.0277   1.0000   0.1616
  -6.500  -0.4324   0.05680   0.05277  -0.0270   1.0000   0.1724
  -6.250  -0.4306   0.05442   0.05031  -0.0260   1.0000   0.1852
  -6.000  -0.4259   0.05200   0.04784  -0.0245   1.0000   0.1988
  -5.750  -0.4193   0.04945   0.04529  -0.0226   1.0000   0.2134
  -4.750  -0.3164   0.02986   0.02264  -0.0255   1.0000   0.0754
  -4.500  -0.2913   0.02694   0.01919  -0.0245   0.9997   0.0665
  -4.250  -0.2456   0.02530   0.01697  -0.0270   0.9932   0.0616
  -4.000  -0.2022   0.02304   0.01438  -0.0291   0.9864   0.0577
  -3.750  -0.1568   0.02152   0.01262  -0.0315   0.9790   0.0545
  -3.500  -0.1125   0.02035   0.01139  -0.0341   0.9707   0.0540
  -3.250  -0.0731   0.01948   0.01045  -0.0362   0.9612   0.0560
  -3.000  -0.0307   0.01871   0.00953  -0.0388   0.9525   0.0688
  -2.750   0.0106   0.01764   0.00899  -0.0412   0.9436   0.1939
  -2.500   0.0984   0.01507   0.00882  -0.0516   0.9445   1.0000
  -2.250   0.1481   0.01498   0.00835  -0.0558   0.9325   1.0000
  -2.000   0.2002   0.01477   0.00789  -0.0603   0.9210   1.0000
  -1.750   0.2519   0.01449   0.00741  -0.0646   0.9101   1.0000
  -1.500   0.2990   0.01419   0.00696  -0.0680   0.8991   1.0000
  -1.250   0.3420   0.01392   0.00658  -0.0705   0.8877   1.0000
  -1.000   0.3765   0.01378   0.00636  -0.0714   0.8748   1.0000
  -0.750   0.4088   0.01367   0.00618  -0.0718   0.8611   1.0000
  -0.500   0.4362   0.01358   0.00604  -0.0710   0.8431   1.0000
  -0.250   0.4642   0.01339   0.00574  -0.0700   0.8218   1.0000
   0.000   0.4874   0.01332   0.00558  -0.0682   0.7985   1.0000
   0.250   0.5110   0.01328   0.00546  -0.0666   0.7768   1.0000
   0.500   0.5329   0.01332   0.00547  -0.0650   0.7561   1.0000
   0.750   0.5556   0.01334   0.00549  -0.0635   0.7357   1.0000
   1.000   0.5776   0.01332   0.00543  -0.0618   0.7116   1.0000
   1.250   0.5991   0.01331   0.00536  -0.0601   0.6840   1.0000
   1.500   0.6210   0.01335   0.00535  -0.0585   0.6553   1.0000
   1.750   0.6430   0.01345   0.00540  -0.0571   0.6254   1.0000
   2.000   0.6648   0.01361   0.00547  -0.0556   0.5925   1.0000
   2.250   0.6861   0.01384   0.00565  -0.0542   0.5570   1.0000
   2.500   0.7073   0.01413   0.00583  -0.0528   0.5221   1.0000
   2.750   0.7286   0.01447   0.00609  -0.0515   0.4889   1.0000
   3.000   0.7463   0.01493   0.00626  -0.0496   0.4355   1.0000
   3.250   0.7653   0.01544   0.00657  -0.0481   0.3944   1.0000
   3.500   0.7858   0.01593   0.00705  -0.0469   0.3668   1.0000
   3.750   0.8041   0.01656   0.00750  -0.0454   0.3272   1.0000
   4.000   0.8237   0.01713   0.00800  -0.0441   0.2894   1.0000
   4.250   0.8436   0.01771   0.00848  -0.0429   0.2251   1.0000
   4.500   0.8560   0.01922   0.00937  -0.0406   0.1354   1.0000
   4.750   0.8612   0.02193   0.01170  -0.0372   0.0595   1.0000
   5.000   0.8735   0.02360   0.01358  -0.0348   0.0490   1.0000
   5.250   0.8855   0.02509   0.01525  -0.0323   0.0452   1.0000
   5.500   0.8984   0.02645   0.01680  -0.0299   0.0424   1.0000
   5.750   0.9122   0.02793   0.01831  -0.0277   0.0409   1.0000
   6.000   0.9318   0.02977   0.02007  -0.0262   0.0396   1.0000
   6.250   0.9622   0.03208   0.02229  -0.0261   0.0389   1.0000
   6.500   0.9988   0.03591   0.02591  -0.0276   0.0363   1.0000
   6.750   1.0235   0.03854   0.02877  -0.0269   0.0352   1.0000
   7.000   1.0536   0.04207   0.03246  -0.0269   0.0363   1.0000
   7.250   1.0668   0.04254   0.03367  -0.0233   0.0395   1.0000
   7.500   1.0854   0.04611   0.03769  -0.0215   0.0437   1.0000
   7.750   1.1177   0.04884   0.04098  -0.0196   0.0612   1.0000
   8.000   1.1315   0.05115   0.04466  -0.0147   0.0873   1.0000
   8.250   1.1240   0.05712   0.05134  -0.0111   0.1004   1.0000
   8.500   1.1127   0.06232   0.05701  -0.0083   0.1074   1.0000
   8.750   1.0837   0.06673   0.06178  -0.0051   0.1093   1.0000
   9.000   1.0562   0.07043   0.06567  -0.0022   0.1098   1.0000
   9.250   1.0271   0.07456   0.06995  -0.0011   0.1098   1.0000
   9.500   0.9991   0.07936   0.07485  -0.0020   0.1091   1.0000
   9.750   0.9709   0.08528   0.08084  -0.0047   0.1082   1.0000
  10.000   0.9452   0.09227   0.08787  -0.0088   0.1073   1.0000
  10.250   0.9173   0.10125   0.09684  -0.0147   0.1066   1.0000
  10.500   0.8879   0.11248   0.10799  -0.0223   0.1065   1.0000
  10.750   0.8582   0.12364   0.11904  -0.0299   0.1081   1.0000
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