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 3 AIRFOIL (fx3-il) Xfoil prediction polar at RE=200,000 Ncrit=0


Details Polar file
Airfoil: WORTMANN FX 3 AIRFOIL (fx3-il)
Reynolds number: 200,000
Max Cl/Cd: 31.68 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx3-il-200000.txt
Download as CSV file: xf-fx3-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 3 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5093   0.11118   0.10811  -0.0739   0.9616   0.0380
 -12.250  -0.5353   0.10406   0.10092  -0.0768   0.9605   0.0374
 -12.000  -0.5676   0.09681   0.09357  -0.0792   0.9596   0.0369
 -11.750  -0.6009   0.09009   0.08671  -0.0806   0.9586   0.0364
 -11.500  -0.6334   0.08392   0.08037  -0.0808   0.9577   0.0359
 -11.250  -0.6650   0.07819   0.07447  -0.0802   0.9569   0.0355
 -11.000  -0.6947   0.07306   0.06913  -0.0789   0.9561   0.0352
 -10.750  -0.9058   0.07020   0.06530  -0.0627   0.9580   0.0314
 -10.500  -0.8876   0.07107   0.06633  -0.0632   0.9569   0.0325
 -10.250  -0.9395   0.06441   0.05910  -0.0551   0.9489   0.0317
 -10.000  -0.9383   0.06171   0.05617  -0.0537   0.9458   0.0321
  -9.750  -0.9296   0.05932   0.05356  -0.0532   0.9438   0.0326
  -9.500  -0.9157   0.05746   0.05146  -0.0532   0.9424   0.0333
  -9.250  -0.8999   0.05564   0.04935  -0.0533   0.9415   0.0342
  -9.000  -0.9087   0.05289   0.04643  -0.0479   0.9356   0.0347
  -8.750  -0.8937   0.05086   0.04406  -0.0470   0.9324   0.0364
  -8.500  -0.8741   0.04915   0.04190  -0.0467   0.9303   0.0381
  -8.250  -0.8534   0.04715   0.03974  -0.0463   0.9292   0.0398
  -8.000  -0.8289   0.04664   0.03919  -0.0468   0.9281   0.0416
  -7.750  -0.8022   0.04640   0.03883  -0.0476   0.9271   0.0445
  -7.500  -0.7744   0.04613   0.03827  -0.0483   0.9264   0.0477
  -7.250  -0.7812   0.04383   0.03603  -0.0424   0.9201   0.0492
  -7.000  -0.7595   0.04332   0.03550  -0.0422   0.9171   0.0523
  -6.750  -0.7332   0.04313   0.03516  -0.0428   0.9150   0.0566
  -6.500  -0.7106   0.04242   0.03448  -0.0421   0.9137   0.0613
  -6.250  -0.6830   0.04246   0.03448  -0.0429   0.9126   0.0668
  -6.000  -0.6567   0.04243   0.03437  -0.0430   0.9118   0.0725
  -5.750  -0.6287   0.04278   0.03477  -0.0438   0.9111   0.0785
  -5.500  -0.6357   0.04080   0.03277  -0.0382   0.9028   0.0811
  -5.250  -0.6098   0.04076   0.03262  -0.0387   0.9003   0.0856
  -5.000  -0.5870   0.04041   0.03239  -0.0382   0.8986   0.0918
  -4.750  -0.5568   0.04063   0.03258  -0.0397   0.8972   0.0983
  -4.500  -0.5260   0.04081   0.03278  -0.0413   0.8962   0.1047
  -4.250  -0.4917   0.04127   0.03327  -0.0440   0.8955   0.1126
  -4.000  -0.4947   0.03951   0.03148  -0.0396   0.8869   0.1160
  -3.750  -0.4602   0.03917   0.03123  -0.0428   0.8846   0.1280
  -3.500  -0.4178   0.03865   0.03106  -0.0484   0.8833   0.1753
  -3.250  -0.4146   0.04206   0.03712  -0.0387   0.8809   0.6229
  -3.000  -0.3665   0.04502   0.03982  -0.0432   0.8799   0.6723
  -2.750  -0.3768   0.04442   0.03921  -0.0360   0.8700   0.6819
  -2.500  -0.3617   0.04641   0.04117  -0.0311   0.8669   0.6950
  -2.250  -0.3399   0.04850   0.04320  -0.0279   0.8652   0.7081
  -2.000  -0.3519   0.04837   0.04310  -0.0196   0.8574   0.7121
  -1.750  -0.3319   0.04926   0.04391  -0.0174   0.8534   0.7239
  -1.500  -0.3056   0.05058   0.04515  -0.0165   0.8511   0.7373
  -1.250  -0.2909   0.05207   0.04663  -0.0109   0.8496   0.7440
  -1.000  -0.2945   0.05122   0.04576  -0.0070   0.8404   0.7540
  -0.750  -0.2686   0.05231   0.04678  -0.0062   0.8373   0.7683
  -0.500  -0.2598   0.05309   0.04757   0.0011   0.8353   0.7786
  -0.250  -0.1594   0.05772   0.05227   0.0006   0.8368   0.8700
   0.000  -0.2664   0.05438   0.04893   0.0213   0.8236   0.8496
   2.000  -0.0796   0.05125   0.04538   0.0197   0.7705   0.8756
   2.250  -0.0422   0.05086   0.04494   0.0170   0.7681   0.8738
   2.500  -0.0067   0.05092   0.04495   0.0110   0.7596   0.8611
   2.750   0.0290   0.05056   0.04456   0.0086   0.7570   0.8603
   3.000   0.0689   0.05039   0.04436   0.0055   0.7554   0.8600
   3.250   0.0836   0.04990   0.04388   0.0060   0.7463   0.8575
   3.500   0.1240   0.04964   0.04361   0.0027   0.7445   0.8559
   3.750   0.1446   0.04954   0.04353   0.0018   0.7360   0.8539
   4.000   0.1833   0.04930   0.04328  -0.0012   0.7337   0.8537
   4.250   0.2263   0.04907   0.04306  -0.0051   0.7323   0.8527
   4.500   0.2539   0.04934   0.04335  -0.0080   0.7232   0.8495
   4.750   0.3070   0.04956   0.04360  -0.0146   0.7213   0.8473
   5.000   0.3510   0.04930   0.04336  -0.0184   0.7199   0.8471
   5.250   0.3647   0.04921   0.04332  -0.0175   0.7103   0.8463
   5.500   0.4023   0.04863   0.04278  -0.0197   0.7082   0.8454
   5.750   0.4424   0.04798   0.04218  -0.0224   0.7067   0.8445
   6.000   0.4595   0.04808   0.04235  -0.0223   0.6965   0.8432
   6.250   0.4998   0.04744   0.04177  -0.0250   0.6942   0.8430
   6.500   0.5426   0.04663   0.04103  -0.0281   0.6927   0.8426
   6.750   0.5620   0.04679   0.04127  -0.0283   0.6820   0.8412
   7.000   0.6041   0.04597   0.04053  -0.0313   0.6797   0.8401
   7.250   0.6470   0.04501   0.03967  -0.0342   0.6780   0.8398
   7.500   0.6743   0.04455   0.03930  -0.0351   0.6672   0.8390
   7.750   0.7345   0.04136   0.03621  -0.0391   0.6635   0.8378
   8.000   0.7858   0.03948   0.03443  -0.0430   0.6612   0.8364
   8.250   0.8171   0.03945   0.03452  -0.0452   0.6491   0.8344
   8.500   0.8680   0.03777   0.03296  -0.0490   0.6453   0.8338
   8.750   0.9016   0.03742   0.03271  -0.0509   0.6321   0.8331
   9.000   0.9501   0.03598   0.03136  -0.0544   0.6159   0.8319
   9.250   0.9926   0.03432   0.02967  -0.0563   0.5859   0.8312
   9.500   1.0314   0.03305   0.02820  -0.0577   0.5373   0.8305
   9.750   1.0502   0.03315   0.02798  -0.0567   0.4771   0.8296
  10.000   1.0533   0.03439   0.02884  -0.0540   0.4125   0.8284
  10.250   1.0506   0.03620   0.03028  -0.0509   0.3483   0.8273
  10.500   1.0464   0.03833   0.03203  -0.0480   0.2834   0.8260
  10.750   1.0438   0.04056   0.03388  -0.0456   0.2223   0.8249
  11.000   1.0455   0.04265   0.03567  -0.0439   0.1750   0.8237
  11.250   1.0525   0.04446   0.03729  -0.0428   0.1438   0.8229
  11.500   1.0616   0.04613   0.03885  -0.0421   0.1200   0.8224
  11.750   1.0708   0.04786   0.04048  -0.0413   0.0980   0.8218
  12.000   1.0756   0.05008   0.04254  -0.0403   0.0743   0.8208
  12.250   1.0829   0.05226   0.04467  -0.0396   0.0575   0.8197
  12.500   1.0917   0.05441   0.04678  -0.0393   0.0495   0.8187
  12.750   1.1039   0.05635   0.04872  -0.0394   0.0442   0.8177
  13.000   1.1135   0.05852   0.05092  -0.0391   0.0410   0.8169
  13.250   1.1234   0.06015   0.05264  -0.0383   0.0383   0.8164
  13.500   1.1318   0.06194   0.05445  -0.0376   0.0361   0.8160
  13.750   1.1401   0.06374   0.05626  -0.0366   0.0342   0.8155
  14.000   1.1529   0.06523   0.05791  -0.0361   0.0326   0.8151
  14.250   1.1660   0.06669   0.05947  -0.0356   0.0312   0.8146
  14.500   1.1796   0.06816   0.06100  -0.0351   0.0300   0.8142
  14.750   1.1938   0.06958   0.06247  -0.0348   0.0289   0.8138
  15.000   1.2151   0.07055   0.06344  -0.0343   0.0275   0.8134
  15.250   1.2304   0.07222   0.06531  -0.0339   0.0267   0.8130
  15.500   1.2405   0.07426   0.06756  -0.0334   0.0260   0.8126
  15.750   1.2510   0.07643   0.06997  -0.0330   0.0255   0.8122
  16.000   1.2589   0.07893   0.07271  -0.0325   0.0250   0.8118
  16.250   1.2633   0.08183   0.07586  -0.0320   0.0246   0.8113
  16.500   1.2641   0.08513   0.07942  -0.0315   0.0244   0.8109
  16.750   1.2607   0.08890   0.08346  -0.0311   0.0243   0.8105
  17.000   1.2536   0.09308   0.08793  -0.0309   0.0241   0.8101
  17.250   1.2431   0.09778   0.09291  -0.0311   0.0240   0.8098
  17.500   1.2300   0.10290   0.09831  -0.0317   0.0240   0.8095
  17.750   1.2150   0.10846   0.10413  -0.0330   0.0238   0.8092
  18.000   1.1949   0.11509   0.11106  -0.0351   0.0240   0.8088
  18.250   1.1735   0.12229   0.11854  -0.0382   0.0241   0.8083
  18.500   1.1479   0.13081   0.12734  -0.0426   0.0244   0.8077
<< Back to WORTMANN FX 3 AIRFOIL (fx3-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 3 AIRFOIL (fx3-il)