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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.43 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66a175-il-1000000.txt
Download as CSV file: xf-fx66a175-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 66-17A-175 AIRFOIL                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.1519   0.09119   0.08807  -0.0749   0.5763   0.0096
 -12.000  -0.3649   0.05681   0.05338  -0.1017   0.6097   0.0052
 -11.750  -0.3973   0.04970   0.04610  -0.1057   0.6065   0.0052
 -11.500  -0.4153   0.04509   0.04135  -0.1080   0.6018   0.0051
 -11.250  -0.4392   0.04010   0.03615  -0.1099   0.5977   0.0052
 -11.000  -0.4645   0.03518   0.03101  -0.1111   0.5939   0.0050
 -10.750  -0.4762   0.03198   0.02762  -0.1115   0.5891   0.0052
 -10.500  -0.4901   0.02917   0.02460  -0.1107   0.5845   0.0051
 -10.250  -0.4988   0.02713   0.02236  -0.1080   0.5804   0.0051
 -10.000  -0.4933   0.02542   0.02045  -0.1066   0.5758   0.0054
  -9.750  -0.4840   0.02381   0.01863  -0.1053   0.5714   0.0054
  -9.500  -0.4685   0.02276   0.01742  -0.1044   0.5671   0.0057
  -9.250  -0.4503   0.02190   0.01643  -0.1037   0.5630   0.0059
  -9.000  -0.4297   0.02137   0.01576  -0.1031   0.5586   0.0060
  -8.750  -0.4187   0.01911   0.01323  -0.1016   0.5550   0.0062
  -8.500  -0.4021   0.01776   0.01180  -0.1006   0.5517   0.0067
  -8.250  -0.3809   0.01701   0.01097  -0.1000   0.5480   0.0068
  -8.000  -0.3578   0.01652   0.01042  -0.0996   0.5441   0.0072
  -7.750  -0.3351   0.01598   0.00979  -0.0991   0.5402   0.0074
  -7.500  -0.3121   0.01535   0.00910  -0.0987   0.5370   0.0078
  -7.250  -0.2884   0.01481   0.00849  -0.0982   0.5335   0.0082
  -7.000  -0.2632   0.01448   0.00808  -0.0980   0.5300   0.0087
  -6.750  -0.2390   0.01405   0.00756  -0.0976   0.5265   0.0092
  -6.500  -0.2183   0.01308   0.00650  -0.0969   0.5239   0.0100
  -6.250  -0.1929   0.01269   0.00607  -0.0967   0.5210   0.0107
  -6.000  -0.1674   0.01230   0.00562  -0.0964   0.5181   0.0112
  -5.750  -0.1417   0.01197   0.00522  -0.0962   0.5151   0.0120
  -5.500  -0.1157   0.01169   0.00485  -0.0960   0.5119   0.0126
  -5.250  -0.0896   0.01133   0.00442  -0.0959   0.5096   0.0137
  -5.000  -0.0632   0.01095   0.00399  -0.0957   0.5073   0.0156
  -4.750  -0.0361   0.01071   0.00372  -0.0957   0.5048   0.0176
  -4.500  -0.0092   0.01044   0.00341  -0.0956   0.5023   0.0228
  -4.250   0.0167   0.01005   0.00311  -0.0954   0.4998   0.0526
  -4.000   0.0415   0.00955   0.00282  -0.0953   0.4969   0.1214
  -3.750   0.0657   0.00877   0.00247  -0.0952   0.4952   0.2398
  -3.500   0.0896   0.00799   0.00219  -0.0950   0.4932   0.3863
  -3.250   0.1180   0.00795   0.00222  -0.0952   0.4911   0.4266
  -3.000   0.1469   0.00800   0.00223  -0.0954   0.4888   0.4436
  -2.750   0.1755   0.00806   0.00226  -0.0955   0.4866   0.4550
  -2.500   0.2041   0.00815   0.00228  -0.0956   0.4843   0.4629
  -2.250   0.2326   0.00827   0.00235  -0.0957   0.4819   0.4705
  -2.000   0.2615   0.00832   0.00239  -0.0959   0.4803   0.4784
  -1.750   0.2903   0.00839   0.00245  -0.0961   0.4785   0.4839
  -1.500   0.3192   0.00849   0.00249  -0.0963   0.4765   0.4885
  -1.250   0.3477   0.00846   0.00244  -0.0965   0.4745   0.4914
  -1.000   0.3761   0.00848   0.00243  -0.0966   0.4723   0.4936
  -0.750   0.4042   0.00854   0.00245  -0.0967   0.4698   0.4959
  -0.500   0.4326   0.00859   0.00246  -0.0969   0.4675   0.4979
  -0.250   0.4613   0.00859   0.00246  -0.0971   0.4656   0.4995
   0.000   0.4900   0.00861   0.00245  -0.0974   0.4637   0.5008
   0.250   0.5185   0.00863   0.00245  -0.0976   0.4618   0.5020
   0.500   0.5469   0.00867   0.00246  -0.0978   0.4598   0.5031
   0.750   0.5751   0.00870   0.00247  -0.0979   0.4578   0.5042
   1.000   0.6028   0.00874   0.00249  -0.0980   0.4553   0.5058
   1.250   0.6308   0.00878   0.00253  -0.0982   0.4533   0.5073
   1.500   0.6592   0.00880   0.00256  -0.0984   0.4518   0.5086
   1.750   0.6875   0.00883   0.00260  -0.0986   0.4501   0.5100
   2.000   0.7157   0.00886   0.00265  -0.0988   0.4485   0.5114
   2.250   0.7438   0.00891   0.00270  -0.0990   0.4468   0.5129
   2.500   0.7718   0.00897   0.00276  -0.0991   0.4451   0.5144
   2.750   0.7995   0.00904   0.00283  -0.0992   0.4434   0.5160
   3.000   0.8271   0.00915   0.00292  -0.0993   0.4415   0.5174
   3.250   0.8547   0.00928   0.00304  -0.0995   0.4395   0.5189
   3.500   0.8826   0.00929   0.00310  -0.0996   0.4385   0.5209
   3.750   0.9104   0.00933   0.00318  -0.0998   0.4373   0.5226
   4.000   0.9382   0.00938   0.00327  -0.0999   0.4360   0.5244
   4.250   0.9659   0.00944   0.00337  -0.1001   0.4346   0.5262
   4.500   0.9935   0.00951   0.00347  -0.1002   0.4332   0.5282
   4.750   1.0211   0.00959   0.00358  -0.1004   0.4318   0.5305
   5.000   1.0485   0.00968   0.00369  -0.1005   0.4305   0.5326
   5.250   1.0756   0.00976   0.00381  -0.1005   0.4291   0.5352
   5.500   1.1026   0.00987   0.00396  -0.1006   0.4276   0.5378
   5.750   1.1296   0.01005   0.00416  -0.1007   0.4258   0.5404
   6.000   1.1567   0.01010   0.00429  -0.1008   0.4243   0.5432
   6.250   1.1835   0.01004   0.00430  -0.1007   0.4203   0.5460
   6.500   1.2102   0.01004   0.00434  -0.1007   0.4166   0.5488
   6.750   1.2354   0.01015   0.00445  -0.1004   0.4113   0.5523
   7.000   1.2625   0.01011   0.00452  -0.1005   0.4069   0.5559
   7.250   1.2883   0.01016   0.00460  -0.1003   0.4007   0.5597
   7.500   1.3138   0.01023   0.00470  -0.1001   0.3912   0.5638
   7.750   1.3349   0.01049   0.00488  -0.0991   0.3696   0.5686
   8.000   1.3246   0.01246   0.00616  -0.0931   0.2497   0.5726
   8.250   1.2991   0.01464   0.00782  -0.0846   0.1605   0.5760
   8.500   1.2633   0.01685   0.00966  -0.0746   0.0875   0.5795
   8.750   1.2418   0.01876   0.01140  -0.0680   0.0450   0.5844
   9.000   1.2117   0.02160   0.01414  -0.0619   0.0093   0.5894
   9.250   1.2119   0.02328   0.01591  -0.0599   0.0067   0.5972
   9.500   1.2139   0.02510   0.01782  -0.0585   0.0059   0.6075
  10.000   1.2140   0.02956   0.02256  -0.0563   0.0050   0.6407
  10.250   1.2149   0.03176   0.02492  -0.0554   0.0048   0.6733
  10.500   1.2325   0.03374   0.02766  -0.0582   0.0045   1.0000
  10.750   1.2315   0.03639   0.03037  -0.0576   0.0040   1.0000
  11.000   1.2294   0.03913   0.03317  -0.0570   0.0038   1.0000
  11.250   1.2280   0.04183   0.03594  -0.0564   0.0039   1.0000
  11.500   1.2232   0.04485   0.03903  -0.0557   0.0037   1.0000
  11.750   1.2212   0.04766   0.04190  -0.0552   0.0038   1.0000
  12.000   1.2036   0.05219   0.04656  -0.0546   0.0033   1.0000
  12.250   1.2127   0.05401   0.04840  -0.0545   0.0035   1.0000
  12.500   1.2017   0.05811   0.05260  -0.0543   0.0034   1.0000
  12.750   1.2005   0.06117   0.05573  -0.0542   0.0032   1.0000
  13.000   1.2005   0.06414   0.05877  -0.0541   0.0032   1.0000
  13.250   1.2011   0.06714   0.06182  -0.0542   0.0031   1.0000
  13.500   1.2001   0.07031   0.06507  -0.0542   0.0030   1.0000
  13.750   1.1985   0.07363   0.06845  -0.0544   0.0030   1.0000
  14.000   1.1988   0.07673   0.07161  -0.0546   0.0030   1.0000
  14.250   1.1969   0.08018   0.07514  -0.0548   0.0029   1.0000
  14.500   1.1997   0.08301   0.07801  -0.0551   0.0030   1.0000
  14.750   1.1991   0.08633   0.08140  -0.0554   0.0029   1.0000
  15.000   1.1993   0.08953   0.08466  -0.0557   0.0030   1.0000
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