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FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il)
Reynolds number: 100,000
Max Cl/Cd: 64.54 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63137sm-il-100000-n5.txt
Download as CSV file: xf-fx63137sm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-137 13.7% smoothed                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1402   0.09392   0.08894  -0.0803   0.9456   0.0378
  -8.500  -0.1262   0.09014   0.08516  -0.0834   0.9399   0.0368
  -8.250  -0.1173   0.08592   0.08096  -0.0867   0.9325   0.0358
  -7.750  -0.1231   0.07183   0.06688  -0.0985   0.9143   0.0326
  -7.500  -0.1175   0.06564   0.06067  -0.1046   0.9077   0.0323
  -7.250  -0.1222   0.05797   0.05294  -0.1125   0.8952   0.0318
  -7.000  -0.1188   0.04746   0.04203  -0.1305   0.8830   0.0314
  -6.750  -0.0870   0.03901   0.03269  -0.1457   0.8769   0.0322
  -6.500  -0.0436   0.03461   0.02770  -0.1540   0.8743   0.0335
  -6.250  -0.0192   0.03260   0.02543  -0.1557   0.8661   0.0342
  -6.000   0.0210   0.02995   0.02236  -0.1602   0.8622   0.0351
  -5.750   0.0634   0.02764   0.01963  -0.1643   0.8593   0.0362
  -5.500   0.1018   0.02584   0.01745  -0.1671   0.8554   0.0378
  -5.250   0.1302   0.02483   0.01634  -0.1678   0.8483   0.0399
  -5.000   0.1673   0.02376   0.01516  -0.1700   0.8440   0.0428
  -4.750   0.2070   0.02259   0.01379  -0.1722   0.8408   0.0452
  -4.500   0.2339   0.02192   0.01318  -0.1725   0.8334   0.0477
  -4.250   0.2688   0.02124   0.01241  -0.1741   0.8280   0.0531
  -4.000   0.3096   0.02044   0.01159  -0.1769   0.8242   0.0597
  -3.750   0.3422   0.01992   0.01106  -0.1783   0.8176   0.0695
  -3.500   0.3798   0.01924   0.01041  -0.1808   0.8117   0.0885
  -3.250   0.4254   0.01825   0.00964  -0.1851   0.8075   0.1507
  -3.000   0.4656   0.01742   0.00949  -0.1888   0.8016   0.3206
  -2.750   0.4968   0.01744   0.00965  -0.1894   0.7948   0.4077
  -2.500   0.5318   0.01750   0.00964  -0.1905   0.7898   0.4560
  -2.250   0.5580   0.01769   0.00981  -0.1899   0.7824   0.4816
  -2.000   0.5878   0.01781   0.00984  -0.1900   0.7759   0.5055
  -1.750   0.6211   0.01788   0.00980  -0.1906   0.7710   0.5293
  -1.500   0.6443   0.01811   0.01001  -0.1896   0.7627   0.5464
  -1.250   0.6747   0.01812   0.00995  -0.1898   0.7567   0.5585
  -1.000   0.7029   0.01819   0.00996  -0.1897   0.7500   0.5689
  -0.750   0.7316   0.01827   0.00995  -0.1899   0.7428   0.5801
  -0.500   0.7632   0.01823   0.00984  -0.1902   0.7375   0.5890
  -0.250   0.7886   0.01840   0.00997  -0.1899   0.7292   0.5995
   0.000   0.8178   0.01842   0.00995  -0.1899   0.7228   0.6083
   0.250   0.8462   0.01851   0.01000  -0.1900   0.7159   0.6184
   0.500   0.8729   0.01861   0.01009  -0.1896   0.7083   0.6276
   0.750   0.9045   0.01861   0.01002  -0.1901   0.7026   0.6376
   1.000   0.9284   0.01881   0.01025  -0.1894   0.6938   0.6475
   1.250   0.9584   0.01883   0.01023  -0.1896   0.6874   0.6573
   1.500   0.9840   0.01902   0.01043  -0.1893   0.6791   0.6684
   1.750   1.0115   0.01908   0.01049  -0.1890   0.6719   0.6778
   2.000   1.0376   0.01924   0.01066  -0.1886   0.6640   0.6888
   2.250   1.0645   0.01935   0.01077  -0.1883   0.6561   0.6999
   2.500   1.0902   0.01949   0.01093  -0.1878   0.6483   0.7107
   2.750   1.1161   0.01963   0.01109  -0.1873   0.6398   0.7227
   3.000   1.1422   0.01977   0.01125  -0.1869   0.6318   0.7351
   3.250   1.1663   0.01992   0.01144  -0.1860   0.6230   0.7471
   3.500   1.1913   0.02007   0.01162  -0.1854   0.6146   0.7601
   3.750   1.2157   0.02023   0.01182  -0.1846   0.6056   0.7740
   4.000   1.2392   0.02042   0.01206  -0.1838   0.5966   0.7889
   4.250   1.2634   0.02055   0.01221  -0.1829   0.5877   0.8046
   4.500   1.2843   0.02076   0.01251  -0.1816   0.5780   0.8215
   4.750   1.3078   0.02084   0.01261  -0.1805   0.5695   0.8407
   5.000   1.3255   0.02107   0.01295  -0.1786   0.5590   0.8636
   5.250   1.3445   0.02112   0.01304  -0.1767   0.5503   0.8961
   5.500   1.3613   0.02124   0.01327  -0.1746   0.5398   1.0000
   5.750   1.3880   0.02163   0.01365  -0.1747   0.5292   1.0000
   6.000   1.4159   0.02194   0.01391  -0.1749   0.5190   1.0000
   6.250   1.4379   0.02240   0.01443  -0.1741   0.5064   1.0000
   6.500   1.4590   0.02282   0.01484  -0.1731   0.4917   1.0000
   6.750   1.4777   0.02325   0.01522  -0.1716   0.4743   1.0000
   7.000   1.4944   0.02375   0.01566  -0.1698   0.4562   1.0000
   7.250   1.5096   0.02432   0.01620  -0.1678   0.4388   1.0000
   7.500   1.5239   0.02494   0.01682  -0.1656   0.4237   1.0000
   7.750   1.5378   0.02563   0.01751  -0.1635   0.4091   1.0000
   8.000   1.5509   0.02637   0.01826  -0.1614   0.3947   1.0000
   8.250   1.5627   0.02720   0.01909  -0.1591   0.3801   1.0000
   8.500   1.5733   0.02811   0.02001  -0.1567   0.3652   1.0000
   8.750   1.5827   0.02913   0.02102  -0.1543   0.3503   1.0000
   9.000   1.5909   0.03026   0.02215  -0.1518   0.3351   1.0000
   9.250   1.5978   0.03152   0.02342  -0.1494   0.3196   1.0000
   9.500   1.6035   0.03292   0.02482  -0.1469   0.3039   1.0000
   9.750   1.6082   0.03447   0.02638  -0.1445   0.2881   1.0000
  10.000   1.6118   0.03618   0.02809  -0.1423   0.2722   1.0000
  10.250   1.6144   0.03806   0.02999  -0.1401   0.2563   1.0000
  10.500   1.6158   0.04014   0.03207  -0.1380   0.2402   1.0000
  10.750   1.6162   0.04243   0.03434  -0.1360   0.2242   1.0000
  11.000   1.6156   0.04491   0.03682  -0.1342   0.2088   1.0000
  11.250   1.6141   0.04758   0.03949  -0.1325   0.1942   1.0000
  11.500   1.6121   0.05044   0.04234  -0.1310   0.1812   1.0000
  11.750   1.6105   0.05336   0.04528  -0.1297   0.1693   1.0000
  12.000   1.6097   0.05632   0.04829  -0.1287   0.1592   1.0000
  12.250   1.6076   0.05951   0.05150  -0.1277   0.1509   1.0000
  12.500   1.6072   0.06262   0.05466  -0.1269   0.1432   1.0000
  12.750   1.6060   0.06589   0.05795  -0.1262   0.1373   1.0000
  13.000   1.6073   0.06897   0.06113  -0.1257   0.1313   1.0000
  13.250   1.6062   0.07236   0.06454  -0.1253   0.1267   1.0000
  13.500   1.6090   0.07534   0.06761  -0.1249   0.1225   1.0000
  13.750   1.6123   0.07830   0.07070  -0.1247   0.1185   1.0000
  14.000   1.6146   0.08140   0.07385  -0.1245   0.1151   1.0000
  14.250   1.6178   0.08433   0.07675  -0.1242   0.1121   1.0000
  14.500   1.6235   0.08707   0.07967  -0.1241   0.1090   1.0000
  14.750   1.6282   0.08995   0.08268  -0.1241   0.1059   1.0000
  15.000   1.6327   0.09283   0.08566  -0.1242   0.1033   1.0000
  15.250   1.6390   0.09539   0.08825  -0.1241   0.1009   1.0000
  15.500   1.6479   0.09755   0.09045  -0.1239   0.0988   1.0000
  15.750   1.6529   0.10047   0.09358  -0.1241   0.0967   1.0000
  16.000   1.6579   0.10337   0.09665  -0.1244   0.0945   1.0000
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