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 2 AIRFOIL (fx2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 2 AIRFOIL (fx2-il)
Reynolds number: 200,000
Max Cl/Cd: 34.2 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx2-il-200000.txt
Download as CSV file: xf-fx2-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 2 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
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.1870   0.08967   0.08510  -0.1910   0.9143   0.0431
 -15.500  -0.2266   0.08110   0.07645  -0.1942   0.9141   0.0418
 -15.250  -0.2744   0.07350   0.06870  -0.1962   0.9138   0.0410
 -15.000  -0.4076   0.06218   0.05670  -0.1933   0.9125   0.0374
 -14.750  -0.4189   0.05996   0.05444  -0.1916   0.9119   0.0379
 -14.500  -0.4490   0.05784   0.05214  -0.1878   0.9113   0.0378
 -14.250  -0.4690   0.05684   0.05107  -0.1835   0.9107   0.0380
 -14.000  -0.5201   0.05833   0.05251  -0.1725   0.9101   0.0374
 -13.750  -0.7057   0.11036   0.10694  -0.0697   0.9924   0.0369
 -13.500  -0.7240   0.10395   0.10045  -0.0724   0.9897   0.0364
 -13.250  -0.7527   0.09687   0.09321  -0.0753   0.9873   0.0361
 -13.000  -0.7768   0.09109   0.08726  -0.0775   0.9853   0.0357
 -12.750  -0.8094   0.08564   0.08160  -0.0777   0.9831   0.0357
 -12.500  -0.8330   0.08079   0.07657  -0.0769   0.9777   0.0352
 -12.250  -0.8606   0.07633   0.07185  -0.0763   0.9747   0.0355
 -12.000  -0.8825   0.07268   0.06792  -0.0755   0.9727   0.0354
 -11.750  -0.9095   0.06929   0.06435  -0.0709   0.9663   0.0353
 -11.500  -0.9277   0.06632   0.06111  -0.0687   0.9621   0.0356
 -11.250  -0.9437   0.06389   0.05835  -0.0664   0.9597   0.0357
 -11.000  -0.9744   0.06192   0.05623  -0.0590   0.9518   0.0359
 -10.750  -0.9833   0.05924   0.05317  -0.0560   0.9481   0.0363
 -10.500  -0.9806   0.05716   0.05070  -0.0545   0.9460   0.0367
 -10.250  -0.9908   0.05517   0.04842  -0.0495   0.9412   0.0370
 -10.000  -0.9838   0.05221   0.04522  -0.0475   0.9368   0.0377
  -9.750  -0.9659   0.05077   0.04374  -0.0472   0.9344   0.0387
  -9.500  -0.9463   0.04996   0.04285  -0.0471   0.9325   0.0400
  -9.250  -0.9240   0.04922   0.04195  -0.0474   0.9310   0.0414
  -9.000  -0.9004   0.04896   0.04139  -0.0478   0.9300   0.0436
  -8.750  -0.9140   0.04685   0.03912  -0.0411   0.9221   0.0442
  -8.500  -0.8911   0.04536   0.03760  -0.0409   0.9200   0.0461
  -8.250  -0.8677   0.04478   0.03701  -0.0410   0.9181   0.0479
  -8.000  -0.8421   0.04450   0.03663  -0.0415   0.9165   0.0506
  -7.750  -0.8150   0.04479   0.03666  -0.0422   0.9153   0.0533
  -7.500  -0.8200   0.04276   0.03475  -0.0368   0.9101   0.0554
  -7.250  -0.8030   0.04209   0.03409  -0.0356   0.9060   0.0582
  -7.000  -0.7801   0.04174   0.03365  -0.0354   0.9035   0.0618
  -6.750  -0.7560   0.04124   0.03316  -0.0353   0.9019   0.0664
  -6.500  -0.7299   0.04127   0.03321  -0.0359   0.9006   0.0719
  -6.250  -0.7031   0.04156   0.03343  -0.0365   0.8997   0.0771
  -6.000  -0.7207   0.03932   0.03123  -0.0293   0.8913   0.0788
  -5.750  -0.6992   0.03892   0.03085  -0.0292   0.8883   0.0850
  -5.500  -0.6742   0.03870   0.03059  -0.0297   0.8864   0.0912
  -5.250  -0.6472   0.03871   0.03064  -0.0309   0.8852   0.0989
  -5.000  -0.6176   0.03905   0.03101  -0.0325   0.8843   0.1084
  -4.750  -0.6305   0.03706   0.02903  -0.0263   0.8755   0.1121
  -4.500  -0.6043   0.03677   0.02880  -0.0272   0.8727   0.1265
  -4.250  -0.5765   0.03623   0.02856  -0.0289   0.8710   0.1713
  -4.000  -0.5584   0.03400   0.02863  -0.0302   0.8699   0.5707
  -3.750  -0.5257   0.03671   0.03148  -0.0297   0.8688   0.6219
  -3.500  -0.5338   0.03558   0.03030  -0.0239   0.8595   0.6342
  -3.250  -0.5055   0.03702   0.03163  -0.0235   0.8564   0.6497
  -3.000  -0.4732   0.03843   0.03290  -0.0244   0.8546   0.6626
  -2.750  -0.4436   0.04104   0.03554  -0.0229   0.8532   0.6704
  -2.500  -0.4501   0.04031   0.03477  -0.0177   0.8447   0.6795
  -2.250  -0.4296   0.04179   0.03628  -0.0149   0.8409   0.6856
  -2.000  -0.4002   0.04312   0.03753  -0.0147   0.8388   0.6963
  -1.750  -0.3712   0.04507   0.03947  -0.0134   0.8373   0.7025
  -1.500  -0.3751   0.04414   0.03848  -0.0098   0.8290   0.7108
  -1.250  -0.3553   0.04503   0.03939  -0.0071   0.8248   0.7148
  -1.000  -0.3236   0.04606   0.04034  -0.0076   0.8225   0.7227
  -0.750  -0.2901   0.04740   0.04164  -0.0080   0.8210   0.7293
  -0.500  -0.3033   0.04653   0.04079  -0.0017   0.8112   0.7331
  -0.250  -0.2642   0.04697   0.04110  -0.0050   0.8077   0.7419
   0.000  -0.2286   0.04774   0.04184  -0.0059   0.8056   0.7442
   0.250  -0.2267   0.04703   0.04113  -0.0019   0.7939   0.7469
   0.500  -0.1719   0.04729   0.04128  -0.0067   0.7902   0.7483
   0.750  -0.1473   0.04632   0.04025  -0.0067   0.7770   0.7505
   1.000  -0.0993   0.04645   0.04030  -0.0108   0.7750   0.7525
   1.250  -0.0884   0.04587   0.03968  -0.0098   0.7642   0.7547
   1.500  -0.0447   0.04583   0.03955  -0.0139   0.7619   0.7568
   1.750  -0.0026   0.04587   0.03954  -0.0169   0.7605   0.7584
   2.000  -0.0011   0.04554   0.03924  -0.0134   0.7499   0.7601
   2.250   0.0345   0.04552   0.03919  -0.0151   0.7479   0.7615
   2.500   0.0740   0.04554   0.03919  -0.0175   0.7466   0.7630
   2.750   0.0787   0.04547   0.03913  -0.0151   0.7362   0.7650
   3.000   0.1164   0.04538   0.03903  -0.0174   0.7343   0.7668
   3.250   0.1576   0.04529   0.03892  -0.0203   0.7330   0.7689
   3.500   0.1662   0.04542   0.03904  -0.0189   0.7228   0.7713
   3.750   0.2066   0.04533   0.03892  -0.0220   0.7208   0.7738
   4.000   0.2424   0.04505   0.03868  -0.0234   0.7195   0.7755
   4.250   0.2471   0.04528   0.03895  -0.0207   0.7093   0.7773
   4.500   0.2825   0.04503   0.03873  -0.0222   0.7072   0.7791
   4.750   0.3205   0.04470   0.03842  -0.0241   0.7057   0.7811
   5.000   0.3295   0.04509   0.03885  -0.0224   0.6957   0.7833
   5.250   0.3662   0.04476   0.03854  -0.0243   0.6934   0.7856
   5.500   0.4061   0.04433   0.03814  -0.0268   0.6919   0.7879
   5.750   0.4472   0.04393   0.03776  -0.0295   0.6905   0.7902
   6.000   0.4532   0.04424   0.03813  -0.0271   0.6793   0.7918
   6.250   0.4892   0.04361   0.03757  -0.0283   0.6776   0.7937
   6.500   0.5268   0.04294   0.03699  -0.0298   0.6765   0.7957
   6.750   0.5352   0.04335   0.03745  -0.0277   0.6649   0.7980
   7.000   0.5767   0.04229   0.03647  -0.0296   0.6632   0.8005
   7.250   0.6234   0.04051   0.03475  -0.0319   0.6604   0.8029
   7.500   0.6498   0.03970   0.03400  -0.0318   0.6500   0.8051
   7.750   0.6956   0.03806   0.03243  -0.0341   0.6481   0.8070
   8.000   0.7360   0.03651   0.03100  -0.0354   0.6467   0.8087
   8.250   0.7497   0.03650   0.03107  -0.0336   0.6351   0.8105
   8.500   0.7902   0.03491   0.02959  -0.0348   0.6327   0.8124
   8.750   0.8113   0.03460   0.02937  -0.0340   0.6220   0.8143
   9.000   0.8535   0.03302   0.02789  -0.0357   0.6169   0.8163
   9.250   0.8792   0.03258   0.02754  -0.0355   0.6037   0.8182
   9.500   0.9145   0.03159   0.02661  -0.0364   0.5884   0.8203
   9.750   0.9553   0.03030   0.02529  -0.0380   0.5634   0.8224
  10.000   0.9906   0.02919   0.02399  -0.0386   0.5182   0.8240
  10.250   1.0051   0.02939   0.02391  -0.0367   0.4647   0.8258
  10.500   1.0076   0.03045   0.02467  -0.0336   0.4127   0.8273
  10.750   1.0042   0.03200   0.02594  -0.0301   0.3626   0.8287
  11.000   0.9992   0.03382   0.02748  -0.0267   0.3119   0.8300
  11.250   0.9917   0.03594   0.02928  -0.0233   0.2599   0.8313
  11.750   0.9837   0.04022   0.03300  -0.0180   0.1699   0.8339
  12.000   0.9856   0.04212   0.03472  -0.0162   0.1398   0.8354
  12.250   0.9902   0.04392   0.03638  -0.0148   0.1176   0.8369
  12.500   0.9964   0.04567   0.03803  -0.0136   0.1005   0.8383
  12.750   1.0003   0.04745   0.03977  -0.0120   0.0885   0.8401
  13.000   1.0021   0.04946   0.04175  -0.0104   0.0769   0.8418
  13.250   1.0030   0.05166   0.04391  -0.0087   0.0676   0.8435
  13.500   1.0110   0.05334   0.04564  -0.0078   0.0599   0.8453
  13.750   1.0179   0.05519   0.04752  -0.0068   0.0545   0.8468
  14.000   1.0277   0.05685   0.04920  -0.0063   0.0504   0.8482
  14.250   1.0370   0.05859   0.05091  -0.0056   0.0474   0.8492
  14.500   1.0496   0.06009   0.05253  -0.0053   0.0444   0.8503
  14.750   1.0612   0.06168   0.05416  -0.0051   0.0422   0.8514
  15.000   1.0751   0.06315   0.05556  -0.0049   0.0398   0.8524
  15.250   1.0889   0.06469   0.05724  -0.0048   0.0382   0.8535
  15.500   1.1037   0.06605   0.05871  -0.0046   0.0367   0.8548
  15.750   1.1171   0.06750   0.06023  -0.0044   0.0353   0.8563
  16.000   1.1329   0.06882   0.06156  -0.0043   0.0342   0.8579
  16.250   1.1537   0.07001   0.06282  -0.0044   0.0328   0.8593
  16.500   1.1638   0.07203   0.06505  -0.0042   0.0319   0.8606
  16.750   1.1736   0.07410   0.06729  -0.0042   0.0309   0.8620
  17.000   1.1841   0.07620   0.06955  -0.0042   0.0301   0.8634
  17.250   1.1934   0.07847   0.07197  -0.0042   0.0294   0.8649
  17.500   1.2021   0.08079   0.07440  -0.0044   0.0288   0.8663
  17.750   1.2122   0.08314   0.07687  -0.0046   0.0283   0.8678
  18.000   1.2249   0.08574   0.07959  -0.0050   0.0277   0.8692
  18.250   1.2227   0.08966   0.08376  -0.0051   0.0274   0.8705
  18.500   1.2126   0.09391   0.08830  -0.0052   0.0273   0.8719
  18.750   1.1978   0.09872   0.09340  -0.0057   0.0272   0.8734
  19.000   1.1829   0.10383   0.09878  -0.0067   0.0271   0.8749
  19.250   1.1664   0.10936   0.10459  -0.0081   0.0270   0.8766
<< Back to WORTMANN FX 2 AIRFOIL (fx2-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 2 AIRFOIL (fx2-il)