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FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 500,000
Max Cl/Cd: 109.8 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100-il-500000.txt
Download as CSV file: xf-fx60100-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2879   0.08431   0.08223  -0.0408   1.0000   0.0195
  -9.250  -0.2935   0.08055   0.07851  -0.0409   1.0000   0.0195
  -9.000  -0.3021   0.07732   0.07532  -0.0398   1.0000   0.0195
  -8.750  -0.3151   0.07473   0.07279  -0.0377   1.0000   0.0195
  -8.500  -0.3277   0.06558   0.06367  -0.0423   0.9983   0.0200
  -8.250  -0.3177   0.06163   0.05973  -0.0451   0.9960   0.0207
  -8.000  -0.3017   0.05900   0.05709  -0.0477   0.9937   0.0219
  -7.750  -0.2974   0.05280   0.05090  -0.0532   0.9893   0.0224
  -7.500  -0.3612   0.05081   0.04841  -0.0817   0.9849   0.0195
  -7.250  -0.3481   0.04027   0.03763  -0.0942   0.9782   0.0209
  -7.000  -0.3180   0.03782   0.03510  -0.0987   0.9750   0.0222
  -6.750  -0.2828   0.03391   0.03088  -0.1049   0.9725   0.0245
  -6.500  -0.2437   0.02840   0.02463  -0.1126   0.9705   0.0286
  -6.250  -0.2162   0.02634   0.02257  -0.1141   0.9654   0.0301
  -6.000  -0.1835   0.02446   0.02050  -0.1164   0.9615   0.0329
  -5.750  -0.1448   0.01755   0.01262  -0.1181   0.9583   0.0174
  -5.500  -0.1113   0.01502   0.00964  -0.1186   0.9547   0.0142
  -5.250  -0.0833   0.01381   0.00830  -0.1186   0.9484   0.0141
  -5.000  -0.0528   0.01246   0.00685  -0.1193   0.9440   0.0144
  -4.750  -0.0238   0.01154   0.00586  -0.1197   0.9387   0.0149
  -4.500   0.0045   0.01092   0.00520  -0.1199   0.9326   0.0161
  -4.250   0.0343   0.01040   0.00461  -0.1202   0.9279   0.0172
  -4.000   0.0623   0.00992   0.00404  -0.1201   0.9210   0.0176
  -3.750   0.0912   0.00952   0.00353  -0.1202   0.9150   0.0183
  -3.500   0.1195   0.00923   0.00313  -0.1200   0.9080   0.0195
  -3.250   0.1484   0.00872   0.00268  -0.1201   0.9012   0.0467
  -3.000   0.1776   0.00763   0.00229  -0.1211   0.8946   0.2492
  -2.750   0.2058   0.00728   0.00218  -0.1213   0.8874   0.3353
  -2.500   0.2338   0.00713   0.00214  -0.1212   0.8799   0.3931
  -2.250   0.2617   0.00705   0.00211  -0.1210   0.8721   0.4279
  -2.000   0.2896   0.00702   0.00205  -0.1208   0.8639   0.4436
  -1.750   0.3177   0.00699   0.00197  -0.1206   0.8560   0.4561
  -1.500   0.3454   0.00696   0.00193  -0.1203   0.8460   0.4698
  -1.250   0.3732   0.00695   0.00188  -0.1201   0.8361   0.4834
  -1.000   0.4008   0.00694   0.00183  -0.1198   0.8244   0.4961
  -0.750   0.4284   0.00694   0.00179  -0.1194   0.8122   0.5105
  -0.500   0.4562   0.00694   0.00178  -0.1192   0.7999   0.5248
  -0.250   0.4839   0.00693   0.00178  -0.1190   0.7876   0.5365
   0.000   0.5117   0.00695   0.00178  -0.1188   0.7749   0.5488
   0.250   0.5393   0.00697   0.00179  -0.1185   0.7606   0.5623
   0.500   0.5665   0.00701   0.00179  -0.1182   0.7428   0.5753
   0.750   0.5937   0.00707   0.00180  -0.1179   0.7231   0.5867
   1.000   0.6208   0.00715   0.00183  -0.1175   0.7012   0.5982
   1.250   0.6477   0.00724   0.00186  -0.1172   0.6798   0.6096
   1.500   0.6748   0.00733   0.00192  -0.1169   0.6593   0.6213
   1.750   0.7016   0.00744   0.00199  -0.1166   0.6390   0.6338
   2.000   0.7286   0.00755   0.00209  -0.1163   0.6179   0.6474
   2.500   0.7816   0.00785   0.00230  -0.1157   0.5723   0.6769
   2.750   0.8079   0.00801   0.00243  -0.1153   0.5500   0.6936
   3.000   0.8342   0.00817   0.00259  -0.1150   0.5274   0.7131
   3.250   0.8603   0.00831   0.00275  -0.1146   0.5057   0.7376
   3.500   0.8859   0.00844   0.00292  -0.1141   0.4829   0.7723
   3.750   0.9093   0.00847   0.00309  -0.1131   0.4613   0.8362
   4.000   0.9300   0.00847   0.00319  -0.1114   0.4364   1.0000
   4.250   0.9561   0.00878   0.00339  -0.1112   0.4094   1.0000
   4.500   0.9817   0.00915   0.00362  -0.1108   0.3777   1.0000
   4.750   1.0065   0.00958   0.00388  -0.1104   0.3412   1.0000
   5.000   1.0310   0.01007   0.00419  -0.1099   0.3009   1.0000
   5.250   1.0552   0.01058   0.00453  -0.1095   0.2649   1.0000
   5.500   1.0792   0.01112   0.00489  -0.1090   0.2284   1.0000
   5.750   1.1028   0.01170   0.00529  -0.1084   0.1923   1.0000
   6.000   1.1263   0.01229   0.00574  -0.1078   0.1632   1.0000
   6.250   1.1497   0.01287   0.00618  -0.1073   0.1371   1.0000
   6.500   1.1737   0.01337   0.00663  -0.1067   0.1213   1.0000
   6.750   1.1975   0.01387   0.00707  -0.1062   0.1046   1.0000
   7.000   1.2206   0.01444   0.00757  -0.1055   0.0915   1.0000
   7.250   1.2441   0.01494   0.00808  -0.1049   0.0802   1.0000
   7.500   1.2671   0.01549   0.00857  -0.1042   0.0680   1.0000
   7.750   1.2893   0.01610   0.00913  -0.1035   0.0587   1.0000
   8.000   1.3096   0.01690   0.00989  -0.1024   0.0514   1.0000
   8.250   1.3329   0.01734   0.01041  -0.1017   0.0482   1.0000
   8.500   1.3552   0.01786   0.01100  -0.1009   0.0442   1.0000
   8.750   1.3747   0.01865   0.01180  -0.0998   0.0398   1.0000
   9.000   1.3976   0.01903   0.01225  -0.0991   0.0378   1.0000
   9.250   1.4197   0.01947   0.01269  -0.0984   0.0344   1.0000
   9.500   1.4395   0.02011   0.01331  -0.0974   0.0299   1.0000
   9.750   1.4613   0.02051   0.01374  -0.0966   0.0256   1.0000
  10.000   1.4801   0.02118   0.01440  -0.0954   0.0190   1.0000
  10.250   1.4927   0.02239   0.01550  -0.0934   0.0092   1.0000
  10.500   1.5044   0.02354   0.01670  -0.0911   0.0070   1.0000
  10.750   1.5152   0.02454   0.01783  -0.0887   0.0063   1.0000
  11.000   1.5239   0.02566   0.01906  -0.0861   0.0059   1.0000
  11.250   1.5309   0.02693   0.02045  -0.0834   0.0055   1.0000
  11.500   1.5352   0.02846   0.02211  -0.0806   0.0051   1.0000
  11.750   1.5359   0.03031   0.02413  -0.0777   0.0049   1.0000
  12.000   1.5390   0.03205   0.02600  -0.0753   0.0048   1.0000
  12.250   1.5417   0.03390   0.02800  -0.0732   0.0047   1.0000
  12.500   1.5427   0.03599   0.03023  -0.0713   0.0046   1.0000
  12.750   1.5424   0.03833   0.03272  -0.0695   0.0046   1.0000
  13.000   1.5404   0.04097   0.03551  -0.0681   0.0045   1.0000
  13.250   1.5370   0.04391   0.03862  -0.0669   0.0045   1.0000
  13.500   1.5325   0.04717   0.04205  -0.0662   0.0044   1.0000
  13.750   1.5265   0.05081   0.04585  -0.0658   0.0044   1.0000
  14.000   1.5193   0.05485   0.05005  -0.0660   0.0043   1.0000
  14.250   1.5107   0.05930   0.05467  -0.0666   0.0043   1.0000
  14.500   1.5013   0.06418   0.05971  -0.0677   0.0043   1.0000
  14.750   1.4907   0.06954   0.06524  -0.0693   0.0043   1.0000
  15.000   1.4791   0.07538   0.07125  -0.0714   0.0043   1.0000
  15.250   1.4667   0.08165   0.07769  -0.0740   0.0043   1.0000
  15.500   1.4535   0.08836   0.08457  -0.0770   0.0043   1.0000
  15.750   1.4397   0.09546   0.09183  -0.0804   0.0043   1.0000
  16.000   1.4255   0.10291   0.09945  -0.0842   0.0043   1.0000
  16.250   1.4102   0.11080   0.10750  -0.0883   0.0043   1.0000
  16.500   1.3954   0.11884   0.11569  -0.0927   0.0043   1.0000
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