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S4062-095-87 (s4062-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4062-095-87 (s4062-il)
Reynolds number: 200,000
Max Cl/Cd: 90.45 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4062-il-200000.txt
Download as CSV file: xf-s4062-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4062-095-87                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3310   0.10736   0.10406  -0.0453   1.0000   0.0397
  -9.250  -0.3485   0.10695   0.10375  -0.0411   1.0000   0.0397
  -9.000  -0.3621   0.10590   0.10276  -0.0390   0.9995   0.0398
  -8.750  -0.3453   0.10035   0.09720  -0.0367   0.9984   0.0415
  -8.500  -0.3248   0.09695   0.09378  -0.0391   0.9954   0.0437
  -8.250  -0.3088   0.09300   0.08982  -0.0438   0.9910   0.0464
  -8.000  -0.2938   0.08832   0.08516  -0.0529   0.9854   0.0493
  -7.750  -0.2793   0.08249   0.07934  -0.0700   0.9743   0.0506
  -7.500  -0.2639   0.07598   0.07284  -0.0740   0.9720   0.0516
  -7.250  -0.2472   0.07347   0.07033  -0.0726   0.9678   0.0530
  -7.000  -0.2250   0.06987   0.06670  -0.0769   0.9632   0.0551
  -6.750  -0.1974   0.06460   0.06139  -0.0866   0.9592   0.0586
  -6.500  -0.1785   0.05391   0.05030  -0.1074   0.9466   0.0637
  -6.250  -0.1549   0.05098   0.04746  -0.1079   0.9443   0.0652
  -6.000  -0.1420   0.04879   0.04525  -0.1077   0.9360   0.0669
  -5.750  -0.1311   0.03375   0.02902  -0.1158   0.9263   0.0414
  -5.500  -0.1128   0.02700   0.02121  -0.1157   0.9195   0.0313
  -5.250  -0.0838   0.02497   0.01872  -0.1161   0.9161   0.0308
  -5.000  -0.0637   0.02290   0.01628  -0.1152   0.9093   0.0309
  -4.750  -0.0386   0.02076   0.01394  -0.1152   0.9049   0.0334
  -4.500  -0.0094   0.01972   0.01272  -0.1153   0.9017   0.0361
  -4.250   0.0137   0.01868   0.01149  -0.1143   0.8955   0.0378
  -4.000   0.0403   0.01756   0.01021  -0.1138   0.8909   0.0405
  -3.750   0.0680   0.01660   0.00924  -0.1136   0.8876   0.0483
  -3.500   0.0918   0.01588   0.00853  -0.1129   0.8819   0.0651
  -3.250   0.1178   0.01530   0.00805  -0.1126   0.8769   0.1007
  -3.000   0.1458   0.01490   0.00774  -0.1125   0.8734   0.1398
  -2.750   0.1712   0.01466   0.00757  -0.1122   0.8685   0.1779
  -2.500   0.1967   0.01439   0.00742  -0.1119   0.8631   0.2204
  -2.250   0.2240   0.01401   0.00722  -0.1118   0.8594   0.2736
  -2.000   0.2504   0.01369   0.00711  -0.1115   0.8556   0.3428
  -1.750   0.2739   0.01344   0.00717  -0.1109   0.8493   0.4311
  -1.250   0.3207   0.01243   0.00707  -0.1082   0.8424   0.7108
  -1.000   0.3553   0.01201   0.00710  -0.1087   0.8370   0.9576
  -0.750   0.3895   0.01202   0.00695  -0.1100   0.8325   1.0000
  -0.500   0.4172   0.01201   0.00680  -0.1097   0.8290   1.0000
  -0.250   0.4424   0.01220   0.00688  -0.1093   0.8231   1.0000
   0.000   0.4689   0.01228   0.00686  -0.1090   0.8177   1.0000
   0.250   0.4971   0.01224   0.00672  -0.1087   0.8141   1.0000
   0.500   0.5222   0.01242   0.00685  -0.1083   0.8075   1.0000
   0.750   0.5494   0.01242   0.00677  -0.1079   0.8021   1.0000
   1.000   0.5783   0.01230   0.00655  -0.1076   0.7983   1.0000
   1.250   0.6028   0.01242   0.00666  -0.1070   0.7895   1.0000
   1.500   0.6316   0.01224   0.00640  -0.1065   0.7846   1.0000
   1.750   0.6567   0.01231   0.00645  -0.1059   0.7758   1.0000
   2.000   0.6854   0.01212   0.00620  -0.1055   0.7702   1.0000
   2.250   0.7108   0.01219   0.00627  -0.1050   0.7616   1.0000
   2.500   0.7394   0.01205   0.00610  -0.1046   0.7558   1.0000
   2.750   0.7650   0.01212   0.00618  -0.1041   0.7470   1.0000
   3.000   0.7937   0.01198   0.00599  -0.1037   0.7408   1.0000
   3.250   0.8192   0.01203   0.00609  -0.1032   0.7311   1.0000
   3.500   0.8469   0.01196   0.00601  -0.1028   0.7234   1.0000
   3.750   0.8736   0.01192   0.00598  -0.1023   0.7137   1.0000
   4.000   0.8997   0.01192   0.00601  -0.1017   0.7032   1.0000
   4.250   0.9266   0.01187   0.00599  -0.1012   0.6927   1.0000
   4.500   0.9535   0.01180   0.00593  -0.1007   0.6813   1.0000
   4.750   0.9796   0.01178   0.00592  -0.1000   0.6679   1.0000
   5.000   1.0049   0.01179   0.00598  -0.0993   0.6525   1.0000
   5.250   1.0296   0.01183   0.00607  -0.0985   0.6343   1.0000
   5.500   1.0542   0.01188   0.00613  -0.0977   0.6135   1.0000
   5.750   1.0781   0.01199   0.00624  -0.0967   0.5888   1.0000
   6.000   1.1008   0.01217   0.00639  -0.0955   0.5573   1.0000
   6.250   1.1216   0.01249   0.00658  -0.0941   0.5158   1.0000
   6.500   1.1393   0.01304   0.00689  -0.0923   0.4645   1.0000
   6.750   1.1546   0.01380   0.00737  -0.0902   0.4106   1.0000
   7.000   1.1686   0.01468   0.00800  -0.0880   0.3641   1.0000
   7.250   1.1833   0.01552   0.00867  -0.0861   0.3254   1.0000
   7.500   1.1979   0.01636   0.00936  -0.0842   0.2934   1.0000
   7.750   1.2124   0.01719   0.01008  -0.0823   0.2648   1.0000
   8.000   1.2263   0.01802   0.01082  -0.0803   0.2383   1.0000
   8.250   1.2392   0.01887   0.01159  -0.0783   0.2126   1.0000
   8.500   1.2493   0.01974   0.01236  -0.0758   0.1883   1.0000
   8.750   1.2591   0.02064   0.01316  -0.0734   0.1640   1.0000
   9.000   1.2695   0.02157   0.01404  -0.0711   0.1422   1.0000
   9.250   1.2786   0.02266   0.01504  -0.0689   0.1231   1.0000
   9.500   1.2878   0.02380   0.01614  -0.0667   0.1050   1.0000
   9.750   1.2963   0.02505   0.01736  -0.0646   0.0880   1.0000
  10.000   1.3026   0.02650   0.01874  -0.0624   0.0731   1.0000
  10.250   1.3061   0.02827   0.02044  -0.0600   0.0601   1.0000
  10.500   1.3094   0.03014   0.02232  -0.0576   0.0500   1.0000
  10.750   1.3129   0.03209   0.02435  -0.0554   0.0435   1.0000
  11.000   1.3153   0.03418   0.02642  -0.0534   0.0392   1.0000
  11.250   1.3214   0.03611   0.02847  -0.0516   0.0362   1.0000
  11.500   1.3291   0.03790   0.03037  -0.0500   0.0336   1.0000
  11.750   1.3359   0.03986   0.03238  -0.0486   0.0318   1.0000
  12.000   1.3434   0.04244   0.03499  -0.0470   0.0299   1.0000
  12.250   1.3551   0.04452   0.03724  -0.0457   0.0288   1.0000
  12.500   1.3645   0.04652   0.03943  -0.0444   0.0276   1.0000
  12.750   1.3725   0.04867   0.04176  -0.0433   0.0264   1.0000
  13.000   1.3782   0.05091   0.04414  -0.0423   0.0252   1.0000
  13.250   1.3841   0.05340   0.04678  -0.0413   0.0244   1.0000
  13.500   1.3897   0.05615   0.04966  -0.0404   0.0238   1.0000
  13.750   1.3947   0.05949   0.05317  -0.0395   0.0231   1.0000
  14.000   1.3939   0.06391   0.05785  -0.0387   0.0227   1.0000
  14.250   1.3837   0.06914   0.06338  -0.0381   0.0224   1.0000
  14.500   1.3718   0.07328   0.06779  -0.0380   0.0223   1.0000
  14.750   1.3583   0.07781   0.07261  -0.0384   0.0222   1.0000
  15.000   1.3431   0.08284   0.07789  -0.0393   0.0220   1.0000
  15.250   1.3264   0.08853   0.08384  -0.0409   0.0220   1.0000
  15.500   1.3087   0.09465   0.09021  -0.0432   0.0218   1.0000
  15.750   1.2896   0.10158   0.09736  -0.0463   0.0219   1.0000
  16.000   1.2700   0.10904   0.10504  -0.0502   0.0219   1.0000
  16.250   1.2492   0.11731   0.11349  -0.0548   0.0220   1.0000
  16.500   1.2281   0.12625   0.12262  -0.0602   0.0222   1.0000
  16.750   1.2062   0.13602   0.13253  -0.0662   0.0224   1.0000
  17.000   1.1914   0.14477   0.14146  -0.0725   0.0227   1.0000
  17.250   1.0785   0.19143   0.18831  -0.1019   0.0295   1.0000
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