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USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 98 AIRFOIL (usa98-il)
Reynolds number: 1,000,000
Max Cl/Cd: 147.37 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa98-il-1000000.txt
Download as CSV file: xf-usa98-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 98 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.0314   0.07660   0.07388  -0.1104   0.8113   0.0435
  -8.000  -0.0204   0.07475   0.07196  -0.1111   0.7996   0.0437
  -7.750  -0.0099   0.07277   0.06994  -0.1119   0.7898   0.0439
  -7.500   0.0004   0.07067   0.06781  -0.1130   0.7818   0.0442
  -7.250   0.0096   0.06839   0.06551  -0.1143   0.7744   0.0445
  -7.000   0.0163   0.06598   0.06306  -0.1156   0.7669   0.0450
  -6.750   0.0023   0.01803   0.01321  -0.1829   0.7612   0.0449
  -6.500   0.0310   0.01744   0.01253  -0.1835   0.7557   0.0453
  -6.250   0.0597   0.01654   0.01146  -0.1842   0.7499   0.0456
  -6.000   0.0885   0.01573   0.01049  -0.1848   0.7443   0.0459
  -5.750   0.1180   0.01499   0.00963  -0.1855   0.7399   0.0462
  -5.500   0.1473   0.01437   0.00890  -0.1859   0.7346   0.0466
  -5.250   0.1764   0.01388   0.00828  -0.1863   0.7292   0.0469
  -5.000   0.2057   0.01347   0.00776  -0.1867   0.7239   0.0472
  -4.750   0.2354   0.01311   0.00735  -0.1870   0.7195   0.0475
  -4.500   0.2649   0.01288   0.00704  -0.1873   0.7143   0.0477
  -4.250   0.2940   0.01204   0.00610  -0.1878   0.7089   0.0483
  -4.000   0.3232   0.01164   0.00567  -0.1881   0.7038   0.0487
  -3.750   0.3529   0.01137   0.00541  -0.1884   0.6992   0.0492
  -3.500   0.3823   0.01118   0.00520  -0.1887   0.6939   0.0497
  -3.250   0.4113   0.01104   0.00501  -0.1888   0.6882   0.0503
  -3.000   0.4408   0.01085   0.00480  -0.1890   0.6831   0.0509
  -2.750   0.4704   0.01063   0.00456  -0.1893   0.6780   0.0514
  -2.500   0.4997   0.01046   0.00435  -0.1895   0.6723   0.0519
  -2.250   0.5286   0.01034   0.00418  -0.1896   0.6662   0.0523
  -2.000   0.5584   0.01019   0.00402  -0.1898   0.6612   0.0528
  -1.750   0.5877   0.01010   0.00391  -0.1899   0.6553   0.0531
  -1.500   0.6170   0.00976   0.00353  -0.1903   0.6493   0.0541
  -1.250   0.6465   0.00963   0.00340  -0.1905   0.6437   0.0549
  -1.000   0.6758   0.00953   0.00330  -0.1907   0.6375   0.0558
  -0.750   0.7047   0.00948   0.00322  -0.1907   0.6309   0.0567
  -0.500   0.7337   0.00944   0.00316  -0.1908   0.6251   0.0577
  -0.250   0.7629   0.00939   0.00310  -0.1909   0.6186   0.0586
   0.000   0.7916   0.00933   0.00300  -0.1910   0.6116   0.0595
   0.250   0.8208   0.00924   0.00291  -0.1911   0.6055   0.0610
   0.500   0.8497   0.00921   0.00287  -0.1912   0.5989   0.0625
   0.750   0.8779   0.00923   0.00286  -0.1911   0.5917   0.0641
   1.000   0.9067   0.00923   0.00285  -0.1912   0.5851   0.0655
   1.250   0.9352   0.00920   0.00281  -0.1912   0.5769   0.0686
   1.500   0.9631   0.00924   0.00283  -0.1911   0.5683   0.0719
   1.750   0.9914   0.00925   0.00283  -0.1910   0.5593   0.0778
   2.000   1.0192   0.00926   0.00287  -0.1909   0.5510   0.0983
   2.250   1.0488   0.00888   0.00297  -0.1915   0.5439   0.2999
   2.500   1.0763   0.00893   0.00308  -0.1913   0.5368   0.3362
   2.750   1.1043   0.00899   0.00317  -0.1913   0.5309   0.3615
   3.000   1.1322   0.00904   0.00327  -0.1912   0.5245   0.3852
   3.250   1.1591   0.00916   0.00339  -0.1909   0.5173   0.4054
   3.500   1.1869   0.00923   0.00350  -0.1908   0.5114   0.4248
   3.750   1.2145   0.00931   0.00361  -0.1906   0.5052   0.4445
   4.000   1.2409   0.00944   0.00375  -0.1902   0.4982   0.4636
   4.250   1.2684   0.00951   0.00386  -0.1901   0.4911   0.4830
   4.500   1.2946   0.00965   0.00400  -0.1896   0.4820   0.5034
   4.750   1.3213   0.00973   0.00415  -0.1894   0.4747   0.5324
   5.000   1.3478   0.00980   0.00431  -0.1890   0.4665   0.5764
   5.250   1.3736   0.00978   0.00454  -0.1887   0.4584   0.7115
   5.500   1.3941   0.00946   0.00466  -0.1869   0.4505   1.0000
   5.750   1.4189   0.00969   0.00483  -0.1863   0.4411   1.0000
   6.000   1.4445   0.00986   0.00498  -0.1857   0.4315   1.0000
   6.250   1.4688   0.01010   0.00517  -0.1850   0.4216   1.0000
   6.500   1.4927   0.01035   0.00536  -0.1841   0.4099   1.0000
   6.750   1.5165   0.01059   0.00557  -0.1833   0.3986   1.0000
   7.000   1.5388   0.01090   0.00581  -0.1822   0.3853   1.0000
   7.250   1.5597   0.01126   0.00608  -0.1808   0.3689   1.0000
   7.500   1.5797   0.01165   0.00639  -0.1792   0.3517   1.0000
   7.750   1.5986   0.01207   0.00672  -0.1775   0.3342   1.0000
   8.000   1.6156   0.01254   0.00710  -0.1754   0.3152   1.0000
   8.250   1.6292   0.01310   0.00754  -0.1726   0.2943   1.0000
   8.500   1.6421   0.01370   0.00804  -0.1698   0.2746   1.0000
   8.750   1.6555   0.01432   0.00857  -0.1671   0.2573   1.0000
   9.000   1.6688   0.01495   0.00911  -0.1644   0.2413   1.0000
   9.250   1.6823   0.01558   0.00967  -0.1619   0.2278   1.0000
   9.500   1.6961   0.01621   0.01026  -0.1594   0.2163   1.0000
   9.750   1.7087   0.01690   0.01089  -0.1568   0.2047   1.0000
  10.000   1.7228   0.01754   0.01149  -0.1545   0.1939   1.0000
  10.250   1.7344   0.01831   0.01222  -0.1519   0.1821   1.0000
  10.500   1.7444   0.01920   0.01304  -0.1491   0.1684   1.0000
  10.750   1.7504   0.02033   0.01407  -0.1458   0.1504   1.0000
  11.000   1.7504   0.02188   0.01548  -0.1419   0.1266   1.0000
  11.250   1.7426   0.02402   0.01743  -0.1371   0.0986   1.0000
  11.750   1.7421   0.02776   0.02105  -0.1306   0.0728   1.0000
  12.000   1.7487   0.02929   0.02259  -0.1285   0.0681   1.0000
  12.250   1.7543   0.03097   0.02428  -0.1264   0.0643   1.0000
  12.500   1.7627   0.03249   0.02583  -0.1247   0.0618   1.0000
  12.750   1.7684   0.03429   0.02765  -0.1230   0.0593   1.0000
  13.000   1.7749   0.03605   0.02945  -0.1213   0.0572   1.0000
  13.250   1.7832   0.03769   0.03114  -0.1199   0.0556   1.0000
  13.500   1.7890   0.03960   0.03308  -0.1184   0.0540   1.0000
  13.750   1.7926   0.04174   0.03526  -0.1169   0.0523   1.0000
  14.000   1.7978   0.04377   0.03733  -0.1155   0.0509   1.0000
  14.250   1.8045   0.04565   0.03928  -0.1143   0.0497   1.0000
  14.500   1.8089   0.04780   0.04148  -0.1131   0.0484   1.0000
  14.750   1.8116   0.05015   0.04386  -0.1118   0.0471   1.0000
  15.000   1.8107   0.05295   0.04670  -0.1105   0.0457   1.0000
  15.250   1.8163   0.05508   0.04891  -0.1095   0.0449   1.0000
  15.500   1.8208   0.05733   0.05121  -0.1086   0.0439   1.0000
  15.750   1.8225   0.05995   0.05389  -0.1076   0.0429   1.0000
  16.000   1.8231   0.06273   0.05672  -0.1068   0.0418   1.0000
  16.250   1.8204   0.06595   0.05998  -0.1059   0.0407   1.0000
  16.500   1.8223   0.06867   0.06278  -0.1052   0.0399   1.0000
  16.750   1.8250   0.07130   0.06547  -0.1046   0.0391   1.0000
  17.000   1.8253   0.07424   0.06847  -0.1040   0.0382   1.0000
  17.250   1.8238   0.07746   0.07175  -0.1035   0.0374   1.0000
  17.500   1.8209   0.08086   0.07521  -0.1031   0.0366   1.0000
  17.750   1.8140   0.08486   0.07927  -0.1028   0.0358   1.0000
  18.000   1.8143   0.08792   0.08241  -0.1026   0.0352   1.0000
  18.250   1.8142   0.09101   0.08558  -0.1024   0.0346   1.0000
  18.500   1.8115   0.09451   0.08915  -0.1023   0.0339   1.0000
  18.750   1.8088   0.09802   0.09272  -0.1023   0.0332   1.0000
  19.000   1.8043   0.10181   0.09656  -0.1025   0.0326   1.0000
  19.250   1.7969   0.10606   0.10088  -0.1028   0.0320   1.0000
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