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

WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il)
Reynolds number: 200,000
Max Cl/Cd: 68.56 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxm2-il-200000-n5.txt
Download as CSV file: xf-fxm2-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX M2 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2755   0.09480   0.09146  -0.0157   1.0000   0.0221
  -7.250  -0.2784   0.09286   0.08958  -0.0151   1.0000   0.0222
  -7.000  -0.2839   0.09112   0.08791  -0.0139   1.0000   0.0222
  -6.750  -0.2717   0.08761   0.08444  -0.0186   0.9964   0.0223
  -6.500  -0.2468   0.08312   0.07995  -0.0266   0.9895   0.0223
  -6.250  -0.2194   0.07847   0.07528  -0.0348   0.9823   0.0224
  -6.000  -0.2047   0.07488   0.07174  -0.0347   0.9753   0.0226
  -5.500  -0.1642   0.06786   0.06473  -0.0412   0.9560   0.0232
  -5.250  -0.1386   0.06407   0.06092  -0.0464   0.9431   0.0237
  -5.000  -0.1060   0.05987   0.05666  -0.0532   0.9288   0.0244
  -4.250   0.0325   0.04498   0.04128  -0.0809   0.8534   0.0279
  -4.000   0.0849   0.04088   0.03675  -0.0889   0.8013   0.0316
  -3.750   0.1260   0.03709   0.03232  -0.0934   0.7446   0.0320
  -3.250   0.1790   0.03035   0.02474  -0.0955   0.6590   0.0271
  -3.000   0.1987   0.02984   0.02411  -0.0952   0.6149   0.0295
  -2.750   0.2256   0.02833   0.02227  -0.0957   0.5872   0.0345
  -2.500   0.2577   0.02559   0.01898  -0.0962   0.5564   0.0312
  -2.250   0.2853   0.02379   0.01679  -0.0964   0.5329   0.0301
  -2.000   0.3148   0.02204   0.01465  -0.0966   0.5018   0.0297
  -1.750   0.3426   0.02075   0.01285  -0.0963   0.4733   0.0300
  -1.500   0.3727   0.01957   0.01113  -0.0961   0.4439   0.0324
  -1.250   0.3994   0.01872   0.00997  -0.0959   0.4173   0.0328
  -1.000   0.4267   0.01798   0.00895  -0.0956   0.3994   0.0332
  -0.750   0.4548   0.01729   0.00808  -0.0953   0.3736   0.0338
  -0.500   0.4815   0.01688   0.00737  -0.0949   0.3538   0.0350
  -0.250   0.5086   0.01661   0.00684  -0.0944   0.3414   0.0373
   0.000   0.5364   0.01625   0.00631  -0.0940   0.3277   0.0380
   0.250   0.5639   0.01571   0.00574  -0.0937   0.3086   0.0388
   0.500   0.5905   0.01543   0.00536  -0.0934   0.2969   0.0398
   0.750   0.6173   0.01529   0.00514  -0.0931   0.2889   0.0421
   1.000   0.6442   0.01521   0.00498  -0.0927   0.2819   0.0443
   1.250   0.6716   0.01511   0.00485  -0.0924   0.2754   0.0452
   1.500   0.6994   0.01495   0.00469  -0.0923   0.2679   0.0468
   1.750   0.7273   0.01487   0.00464  -0.0922   0.2595   0.0495
   2.000   0.7547   0.01492   0.00462  -0.0919   0.2515   0.0532
   2.500   0.8087   0.01512   0.00467  -0.0913   0.2395   0.0611
   2.750   0.8352   0.01529   0.00477  -0.0910   0.2343   0.0791
   3.000   0.8510   0.01372   0.00504  -0.0884   0.2298   1.0000
   3.250   0.8769   0.01408   0.00525  -0.0880   0.2238   1.0000
   3.500   0.9034   0.01437   0.00545  -0.0876   0.2176   1.0000
   3.750   0.9299   0.01465   0.00566  -0.0872   0.2112   1.0000
   4.000   0.9570   0.01484   0.00583  -0.0870   0.2054   1.0000
   4.250   0.9838   0.01506   0.00604  -0.0866   0.1995   1.0000
   4.500   1.0103   0.01530   0.00625  -0.0863   0.1953   1.0000
   4.750   1.0367   0.01555   0.00646  -0.0859   0.1911   1.0000
   5.000   1.0629   0.01581   0.00667  -0.0856   0.1868   1.0000
   5.250   1.0888   0.01609   0.00691  -0.0852   0.1829   1.0000
   5.500   1.1146   0.01639   0.00719  -0.0848   0.1790   1.0000
   5.750   1.1401   0.01672   0.00747  -0.0844   0.1752   1.0000
   6.000   1.1651   0.01709   0.00779  -0.0839   0.1717   1.0000
   6.250   1.1906   0.01741   0.00814  -0.0835   0.1685   1.0000
   6.500   1.2160   0.01774   0.00853  -0.0830   0.1651   1.0000
   6.750   1.2410   0.01810   0.00891  -0.0825   0.1614   1.0000
   7.000   1.2654   0.01850   0.00931  -0.0820   0.1577   1.0000
   7.250   1.2897   0.01891   0.00973  -0.0815   0.1543   1.0000
   7.500   1.3148   0.01923   0.01016  -0.0810   0.1505   1.0000
   7.750   1.3392   0.01961   0.01058  -0.0805   0.1458   1.0000
   8.000   1.3630   0.02003   0.01102  -0.0799   0.1412   1.0000
   8.250   1.3870   0.02043   0.01148  -0.0794   0.1369   1.0000
   8.500   1.4106   0.02085   0.01197  -0.0788   0.1318   1.0000
   8.750   1.4335   0.02131   0.01245  -0.0781   0.1270   1.0000
   9.000   1.4561   0.02180   0.01298  -0.0774   0.1232   1.0000
   9.250   1.4782   0.02232   0.01355  -0.0767   0.1195   1.0000
   9.500   1.4997   0.02288   0.01415  -0.0759   0.1161   1.0000
   9.750   1.5202   0.02349   0.01479  -0.0750   0.1132   1.0000
  10.000   1.5409   0.02409   0.01547  -0.0741   0.1109   1.0000
  10.250   1.5611   0.02472   0.01621  -0.0731   0.1087   1.0000
  10.500   1.5805   0.02538   0.01696  -0.0721   0.1067   1.0000
  10.750   1.5990   0.02608   0.01775  -0.0709   0.1048   1.0000
  11.000   1.6165   0.02683   0.01858  -0.0697   0.1031   1.0000
  11.250   1.6327   0.02763   0.01948  -0.0683   0.1015   1.0000
  11.500   1.6473   0.02850   0.02043  -0.0668   0.1002   1.0000
  11.750   1.6595   0.02943   0.02143  -0.0649   0.0990   1.0000
  12.000   1.6720   0.03028   0.02242  -0.0630   0.0981   1.0000
  12.250   1.6831   0.03120   0.02349  -0.0611   0.0971   1.0000
  12.500   1.6933   0.03219   0.02463  -0.0591   0.0957   1.0000
  12.750   1.7020   0.03328   0.02586  -0.0572   0.0942   1.0000
  13.000   1.7092   0.03451   0.02723  -0.0553   0.0928   1.0000
  13.250   1.7147   0.03590   0.02875  -0.0535   0.0914   1.0000
  13.500   1.7185   0.03750   0.03046  -0.0518   0.0900   1.0000
  13.750   1.7202   0.03936   0.03245  -0.0503   0.0888   1.0000
  14.000   1.7197   0.04156   0.03475  -0.0491   0.0877   1.0000
  14.250   1.7198   0.04390   0.03724  -0.0483   0.0868   1.0000
  14.500   1.7196   0.04648   0.03998  -0.0480   0.0858   1.0000
  14.750   1.7176   0.04943   0.04311  -0.0480   0.0850   1.0000
  15.000   1.7139   0.05281   0.04666  -0.0485   0.0841   1.0000
  15.250   1.7083   0.05664   0.05067  -0.0494   0.0833   1.0000
  15.500   1.7008   0.06097   0.05517  -0.0508   0.0825   1.0000
  15.750   1.6912   0.06583   0.06019  -0.0527   0.0818   1.0000
  16.000   1.6796   0.07118   0.06571  -0.0550   0.0811   1.0000
  16.250   1.6657   0.07708   0.07177  -0.0577   0.0804   1.0000
  16.500   1.6507   0.08330   0.07814  -0.0606   0.0797   1.0000
  16.750   1.6351   0.08980   0.08478  -0.0638   0.0791   1.0000
  17.000   1.6209   0.09616   0.09125  -0.0670   0.0784   1.0000
  17.250   1.6095   0.10209   0.09729  -0.0700   0.0776   1.0000
  17.500   1.5984   0.10809   0.10338  -0.0730   0.0768   1.0000
  17.750   1.5779   0.11629   0.11180  -0.0777   0.0761   1.0000
  18.000   1.5545   0.12533   0.12105  -0.0831   0.0754   1.0000
  18.250   1.5276   0.13534   0.13126  -0.0893   0.0744   1.0000
  18.500   1.4894   0.14827   0.14441  -0.0977   0.0731   1.0000
<< Back to WORTMANN FX M2 AIRFOIL (fxm2-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX M2 AIRFOIL (fxm2-il)