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

FX S 03-182 AIRFOIL (fxs03182-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX S 03-182 AIRFOIL (fxs03182-il)
Reynolds number: 200,000
Max Cl/Cd: 66.69 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxs03182-il-200000-n5.txt
Download as CSV file: xf-fxs03182-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX S 03-182 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.4986   0.08776   0.08394  -0.0800   1.0000   0.0057
 -14.000  -0.5255   0.07877   0.07478  -0.0848   1.0000   0.0057
 -13.750  -0.5435   0.07046   0.06626  -0.0903   0.9902   0.0056
 -13.500  -0.5495   0.06423   0.05980  -0.0957   0.9762   0.0056
 -13.250  -0.5540   0.05847   0.05377  -0.1009   0.9615   0.0056
 -13.000  -0.5505   0.05367   0.04868  -0.1060   0.9491   0.0055
 -12.750  -0.5464   0.04885   0.04353  -0.1109   0.9358   0.0056
 -12.500  -0.5380   0.04455   0.03889  -0.1154   0.9222   0.0056
 -12.250  -0.5279   0.04070   0.03466  -0.1190   0.9078   0.0058
 -12.000  -0.5081   0.03861   0.03232  -0.1218   0.8937   0.0057
 -11.750  -0.4950   0.03636   0.02981  -0.1232   0.8794   0.0058
 -11.500  -0.4813   0.03458   0.02780  -0.1239   0.8662   0.0058
 -11.250  -0.4722   0.03272   0.02574  -0.1238   0.8542   0.0061
 -11.000  -0.4589   0.03156   0.02440  -0.1235   0.8431   0.0060
 -10.750  -0.4484   0.03023   0.02290  -0.1228   0.8332   0.0062
 -10.500  -0.4369   0.02903   0.02153  -0.1220   0.8244   0.0064
 -10.250  -0.4255   0.02800   0.02036  -0.1210   0.8152   0.0065
 -10.000  -0.4137   0.02697   0.01919  -0.1199   0.8076   0.0068
  -9.750  -0.4009   0.02612   0.01817  -0.1188   0.7998   0.0068
  -9.500  -0.3877   0.02529   0.01721  -0.1177   0.7933   0.0069
  -9.250  -0.3758   0.02440   0.01620  -0.1164   0.7868   0.0074
  -8.750  -0.3490   0.02292   0.01452  -0.1140   0.7756   0.0082
  -8.500  -0.3356   0.02223   0.01381  -0.1128   0.7703   0.0091
  -8.250  -0.3215   0.02160   0.01318  -0.1116   0.7658   0.0105
  -8.000  -0.3075   0.02103   0.01255  -0.1103   0.7606   0.0132
  -7.750  -0.2938   0.02046   0.01185  -0.1088   0.7559   0.0156
  -7.500  -0.2815   0.01991   0.01120  -0.1071   0.7518   0.0177
  -7.250  -0.2698   0.01949   0.01070  -0.1052   0.7470   0.0195
  -7.000  -0.2558   0.01910   0.01021  -0.1037   0.7428   0.0214
  -6.750  -0.2417   0.01857   0.00970  -0.1024   0.7394   0.0266
  -6.500  -0.2242   0.01820   0.00927  -0.1014   0.7360   0.0298
  -6.250  -0.2052   0.01789   0.00890  -0.1005   0.7323   0.0350
  -6.000  -0.1858   0.01755   0.00850  -0.0997   0.7290   0.0418
  -5.750  -0.1668   0.01713   0.00810  -0.0990   0.7262   0.0509
  -5.500  -0.1462   0.01673   0.00770  -0.0985   0.7237   0.0679
  -5.250  -0.1280   0.01622   0.00732  -0.0978   0.7205   0.0998
  -5.000  -0.1110   0.01548   0.00686  -0.0971   0.7172   0.1598
  -4.750  -0.0973   0.01417   0.00616  -0.0965   0.7142   0.2990
  -4.500  -0.0791   0.01312   0.00592  -0.0963   0.7116   0.4702
  -4.250  -0.0515   0.01326   0.00617  -0.0962   0.7096   0.5358
  -4.000  -0.0235   0.01341   0.00624  -0.0965   0.7072   0.5661
  -3.750   0.0040   0.01372   0.00653  -0.0964   0.7046   0.5912
  -3.500   0.0314   0.01414   0.00690  -0.0961   0.7023   0.6108
  -3.250   0.0586   0.01457   0.00731  -0.0957   0.7001   0.6254
  -3.000   0.0860   0.01488   0.00758  -0.0954   0.6982   0.6335
  -2.750   0.1146   0.01495   0.00754  -0.0958   0.6964   0.6397
  -2.250   0.1697   0.01512   0.00761  -0.0960   0.6924   0.6460
  -2.000   0.1974   0.01509   0.00751  -0.0964   0.6900   0.6487
  -1.750   0.2261   0.01502   0.00736  -0.0971   0.6878   0.6515
  -1.500   0.2546   0.01500   0.00727  -0.0976   0.6860   0.6536
  -1.250   0.2826   0.01504   0.00727  -0.0979   0.6843   0.6552
  -1.000   0.3111   0.01506   0.00726  -0.0983   0.6827   0.6569
  -0.750   0.3401   0.01508   0.00723  -0.0989   0.6813   0.6587
  -0.500   0.3688   0.01511   0.00722  -0.0994   0.6799   0.6605
  -0.250   0.3956   0.01514   0.00726  -0.0997   0.6776   0.6623
   0.000   0.4232   0.01517   0.00727  -0.1002   0.6754   0.6642
   0.250   0.4517   0.01520   0.00727  -0.1008   0.6735   0.6665
   0.500   0.4800   0.01524   0.00731  -0.1013   0.6718   0.6682
   0.750   0.5079   0.01530   0.00738  -0.1017   0.6702   0.6694
   1.000   0.5364   0.01536   0.00745  -0.1021   0.6687   0.6706
   1.250   0.5655   0.01541   0.00750  -0.1027   0.6672   0.6720
   1.500   0.5951   0.01548   0.00755  -0.1034   0.6659   0.6735
   1.750   0.6203   0.01562   0.00777  -0.1034   0.6638   0.6752
   2.000   0.6464   0.01575   0.00796  -0.1035   0.6617   0.6773
   2.250   0.6734   0.01587   0.00812  -0.1038   0.6595   0.6794
   2.500   0.7013   0.01598   0.00826  -0.1043   0.6575   0.6814
   2.750   0.7291   0.01609   0.00841  -0.1047   0.6559   0.6829
   3.000   0.7571   0.01619   0.00857  -0.1051   0.6543   0.6842
   3.250   0.7861   0.01628   0.00871  -0.1057   0.6527   0.6856
   3.500   0.8150   0.01639   0.00887  -0.1062   0.6511   0.6872
   3.750   0.8360   0.01660   0.00922  -0.1054   0.6471   0.6892
   4.000   0.8616   0.01664   0.00934  -0.1053   0.6428   0.6914
   4.250   0.8934   0.01633   0.00899  -0.1060   0.6361   0.6937
   4.500   0.9152   0.01621   0.00894  -0.1050   0.6267   0.6960
   4.750   0.9378   0.01595   0.00871  -0.1040   0.6149   0.6978
   5.000   0.9599   0.01575   0.00857  -0.1029   0.6029   0.6995
   5.250   0.9827   0.01564   0.00849  -0.1020   0.5921   0.7013
   5.500   1.0029   0.01565   0.00858  -0.1007   0.5809   0.7035
   5.750   1.0218   0.01574   0.00878  -0.0993   0.5700   0.7058
   6.000   1.0403   0.01582   0.00893  -0.0979   0.5567   0.7085
   6.500   1.0671   0.01600   0.00914  -0.0929   0.5068   0.7137
   6.750   1.0603   0.01653   0.00931  -0.0867   0.4439   0.7163
   7.000   1.0424   0.01791   0.01032  -0.0797   0.3849   0.7193
   7.250   1.0250   0.01966   0.01177  -0.0736   0.3329   0.7225
   7.500   1.0114   0.02160   0.01345  -0.0687   0.2852   0.7258
   7.750   0.9992   0.02369   0.01532  -0.0645   0.2371   0.7283
   8.000   0.9955   0.02549   0.01698  -0.0616   0.2010   0.7311
   8.250   0.9966   0.02714   0.01852  -0.0593   0.1738   0.7342
   8.500   0.9997   0.02876   0.02003  -0.0575   0.1458   0.7377
   8.750   1.0032   0.03042   0.02160  -0.0558   0.1231   0.7412
   9.000   1.0067   0.03206   0.02317  -0.0540   0.0967   0.7443
   9.250   1.0121   0.03366   0.02469  -0.0526   0.0765   0.7481
   9.500   1.0115   0.03579   0.02660  -0.0509   0.0468   0.7521
   9.750   1.0216   0.03716   0.02798  -0.0500   0.0350   0.7563
  10.000   1.0297   0.03866   0.02947  -0.0489   0.0295   0.7600
  10.250   1.0416   0.03992   0.03079  -0.0482   0.0263   0.7643
  10.500   1.0560   0.04103   0.03200  -0.0478   0.0238   0.7693
  10.750   1.0695   0.04217   0.03330  -0.0472   0.0209   0.7737
  11.000   1.0807   0.04355   0.03475  -0.0466   0.0176   0.7788
  11.250   1.0913   0.04507   0.03630  -0.0461   0.0157   0.7845
  11.500   1.1025   0.04648   0.03780  -0.0454   0.0147   0.7898
  11.750   1.1131   0.04799   0.03939  -0.0449   0.0132   0.7962
  12.000   1.1231   0.04958   0.04106  -0.0444   0.0118   0.8026
  12.250   1.1331   0.05117   0.04275  -0.0438   0.0109   0.8100
  12.500   1.1430   0.05278   0.04447  -0.0433   0.0104   0.8179
  12.750   1.1525   0.05446   0.04627  -0.0428   0.0098   0.8271
  13.000   1.1615   0.05613   0.04809  -0.0422   0.0094   0.8374
  13.250   1.1714   0.05769   0.04979  -0.0417   0.0090   0.8497
  13.500   1.1802   0.05927   0.05154  -0.0410   0.0087   0.8650
  14.000   1.1885   0.06201   0.05469  -0.0379   0.0069   0.9892
  14.250   1.1989   0.06406   0.05688  -0.0381   0.0056   1.0000
  14.500   1.2068   0.06632   0.05921  -0.0383   0.0044   1.0000
  14.750   1.2140   0.06867   0.06162  -0.0385   0.0040   1.0000
  15.000   1.2200   0.07121   0.06422  -0.0387   0.0038   1.0000
  15.250   1.2259   0.07380   0.06690  -0.0390   0.0037   1.0000
  15.500   1.2307   0.07656   0.06978  -0.0394   0.0036   1.0000
  15.750   1.2355   0.07936   0.07269  -0.0398   0.0035   1.0000
  16.000   1.2391   0.08235   0.07580  -0.0403   0.0034   1.0000
  16.250   1.2423   0.08547   0.07905  -0.0409   0.0034   1.0000
  16.500   1.2445   0.08876   0.08247  -0.0416   0.0033   1.0000
  16.750   1.2457   0.09225   0.08610  -0.0424   0.0033   1.0000
  17.000   1.2462   0.09590   0.08989  -0.0434   0.0032   1.0000
  17.250   1.2452   0.09984   0.09398  -0.0446   0.0032   1.0000
  17.500   1.2439   0.10390   0.09819  -0.0460   0.0032   1.0000
  17.750   1.2414   0.10825   0.10269  -0.0476   0.0031   1.0000
  18.000   1.2376   0.11285   0.10745  -0.0494   0.0031   1.0000
  18.250   1.2331   0.11768   0.11244  -0.0515   0.0030   1.0000
  18.500   1.2277   0.12274   0.11766  -0.0538   0.0030   1.0000
  18.750   1.2207   0.12820   0.12328  -0.0565   0.0030   1.0000
  19.000   1.2135   0.13382   0.12906  -0.0595   0.0029   1.0000
  19.250   1.2060   0.13964   0.13504  -0.0627   0.0029   1.0000
<< Back to FX S 03-182 AIRFOIL (fxs03182-il)

Polar data table (+)

Polar graphs


<< Back to FX S 03-182 AIRFOIL (fxs03182-il)