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USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 98 AIRFOIL (usa98-il)
Reynolds number: 100,000
Max Cl/Cd: 59.73 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa98-il-100000-n5.txt
Download as CSV file: xf-usa98-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.0770   0.09984   0.09420  -0.0790   0.9264   0.0983
  -7.500  -0.0908   0.09746   0.09183  -0.0860   0.9086   0.1019
  -7.250  -0.0850   0.09376   0.08813  -0.0903   0.8978   0.1024
  -7.000  -0.0578   0.09011   0.08447  -0.0902   0.8923   0.1032
  -6.750  -0.0325   0.08685   0.08117  -0.0919   0.8869   0.1042
  -6.500  -0.0150   0.08403   0.07834  -0.0935   0.8780   0.1053
  -6.000   0.0011   0.06979   0.06384  -0.1130   0.8579   0.0812
  -5.750   0.0272   0.06728   0.06129  -0.1152   0.8525   0.0818
  -5.250   0.0820   0.04506   0.03825  -0.1499   0.8360   0.0718
  -5.000   0.1191   0.03993   0.03267  -0.1586   0.8303   0.0716
  -4.750   0.1536   0.03584   0.02804  -0.1652   0.8226   0.0724
  -4.500   0.1867   0.03431   0.02645  -0.1675   0.8166   0.0732
  -4.250   0.2215   0.03239   0.02426  -0.1707   0.8106   0.0739
  -4.000   0.2530   0.03051   0.02207  -0.1731   0.8031   0.0742
  -3.750   0.2881   0.02886   0.02007  -0.1757   0.7970   0.0746
  -3.500   0.3220   0.02754   0.01846  -0.1776   0.7910   0.0751
  -3.250   0.3512   0.02654   0.01725  -0.1785   0.7835   0.0757
  -3.000   0.3838   0.02561   0.01608  -0.1798   0.7772   0.0765
  -2.750   0.4160   0.02486   0.01510  -0.1809   0.7714   0.0781
  -2.500   0.4440   0.02429   0.01434  -0.1811   0.7638   0.0796
  -2.250   0.4752   0.02372   0.01353  -0.1817   0.7575   0.0807
  -2.000   0.5065   0.02307   0.01282  -0.1824   0.7521   0.0816
  -1.750   0.5323   0.02267   0.01244  -0.1821   0.7445   0.0826
  -1.500   0.5615   0.02226   0.01200  -0.1824   0.7381   0.0838
  -1.250   0.5929   0.02188   0.01155  -0.1829   0.7331   0.0853
  -1.000   0.6180   0.02169   0.01139  -0.1824   0.7254   0.0874
  -0.750   0.6464   0.02149   0.01113  -0.1824   0.7189   0.0901
  -0.500   0.6771   0.02118   0.01082  -0.1828   0.7138   0.0926
  -0.250   0.7028   0.02105   0.01077  -0.1824   0.7067   0.0949
   0.000   0.7306   0.02092   0.01063  -0.1823   0.7000   0.0977
   0.250   0.7611   0.02077   0.01040  -0.1827   0.6947   0.1011
   0.500   0.7875   0.02069   0.01038  -0.1824   0.6880   0.1060
   0.750   0.8149   0.02064   0.01034  -0.1823   0.6812   0.1135
   1.000   0.8453   0.02046   0.01016  -0.1827   0.6758   0.1248
   1.250   0.8731   0.02027   0.01016  -0.1827   0.6695   0.1570
   1.500   0.8998   0.02009   0.01056  -0.1827   0.6626   0.3335
   1.750   0.9284   0.02018   0.01070  -0.1826   0.6570   0.3924
   2.000   0.9550   0.02034   0.01091  -0.1822   0.6510   0.4283
   2.250   0.9796   0.02053   0.01119  -0.1814   0.6439   0.4604
   2.500   1.0071   0.02060   0.01132  -0.1811   0.6382   0.5033
   2.750   1.0334   0.02067   0.01149  -0.1806   0.6325   0.5398
   3.000   1.0571   0.02083   0.01174  -0.1797   0.6252   0.5645
   3.500   1.1102   0.02090   0.01195  -0.1788   0.6135   0.6229
   3.750   1.1316   0.02094   0.01224  -0.1774   0.6061   0.6874
   4.000   1.1534   0.02059   0.01213  -0.1757   0.6001   1.0000
   4.250   1.1783   0.02086   0.01233  -0.1750   0.5924   1.0000
   4.500   1.2028   0.02108   0.01248  -0.1742   0.5836   1.0000
   4.750   1.2288   0.02126   0.01256  -0.1736   0.5756   1.0000
   5.000   1.2509   0.02156   0.01285  -0.1724   0.5664   1.0000
   5.250   1.2792   0.02171   0.01288  -0.1722   0.5599   1.0000
   5.500   1.2987   0.02215   0.01338  -0.1707   0.5513   1.0000
   5.750   1.3236   0.02240   0.01359  -0.1700   0.5441   1.0000
   6.000   1.3467   0.02274   0.01392  -0.1690   0.5368   1.0000
   6.250   1.3677   0.02312   0.01432  -0.1677   0.5286   1.0000
   6.500   1.3942   0.02334   0.01446  -0.1673   0.5220   1.0000
   6.750   1.4112   0.02386   0.01507  -0.1653   0.5131   1.0000
   7.000   1.4346   0.02415   0.01533  -0.1643   0.5056   1.0000
   7.250   1.4527   0.02462   0.01587  -0.1626   0.4970   1.0000
   7.500   1.4726   0.02501   0.01627  -0.1610   0.4886   1.0000
   7.750   1.4915   0.02546   0.01674  -0.1594   0.4804   1.0000
   8.000   1.5078   0.02595   0.01728  -0.1573   0.4714   1.0000
   8.250   1.5248   0.02640   0.01775  -0.1553   0.4622   1.0000
   8.500   1.5371   0.02692   0.01830  -0.1525   0.4517   1.0000
   8.750   1.5468   0.02751   0.01894  -0.1493   0.4409   1.0000
   9.000   1.5599   0.02802   0.01941  -0.1467   0.4301   1.0000
   9.250   1.5656   0.02886   0.02034  -0.1431   0.4179   1.0000
   9.500   1.5737   0.02964   0.02113  -0.1400   0.4057   1.0000
   9.750   1.5825   0.03044   0.02188  -0.1370   0.3937   1.0000
  10.000   1.5868   0.03155   0.02307  -0.1337   0.3809   1.0000
  10.250   1.5923   0.03266   0.02422  -0.1307   0.3685   1.0000
  10.500   1.5976   0.03384   0.02537  -0.1278   0.3563   1.0000
  10.750   1.6005   0.03526   0.02681  -0.1248   0.3432   1.0000
  11.000   1.6027   0.03683   0.02841  -0.1220   0.3300   1.0000
  11.250   1.6045   0.03853   0.03010  -0.1194   0.3173   1.0000
  11.500   1.6056   0.04035   0.03190  -0.1169   0.3050   1.0000
  11.750   1.6065   0.04234   0.03393  -0.1146   0.2930   1.0000
  12.000   1.6082   0.04436   0.03598  -0.1126   0.2825   1.0000
  12.250   1.6088   0.04649   0.03809  -0.1105   0.2723   1.0000
  12.500   1.6091   0.04878   0.04046  -0.1087   0.2619   1.0000
  12.750   1.6085   0.05118   0.04288  -0.1069   0.2521   1.0000
  13.000   1.6071   0.05376   0.04550  -0.1053   0.2418   1.0000
  13.250   1.6056   0.05645   0.04824  -0.1039   0.2320   1.0000
  13.500   1.6022   0.05933   0.05112  -0.1024   0.2222   1.0000
  13.750   1.5991   0.06240   0.05428  -0.1013   0.2117   1.0000
  14.000   1.5946   0.06565   0.05757  -0.1002   0.2014   1.0000
  14.250   1.5880   0.06921   0.06116  -0.0992   0.1907   1.0000
  14.500   1.5821   0.07289   0.06493  -0.0986   0.1789   1.0000
  14.750   1.5747   0.07683   0.06892  -0.0980   0.1670   1.0000
  15.000   1.5658   0.08105   0.07317  -0.0977   0.1548   1.0000
  15.250   1.5559   0.08551   0.07763  -0.0975   0.1430   1.0000
  15.500   1.5453   0.09016   0.08227  -0.0976   0.1321   1.0000
  15.750   1.5357   0.09475   0.08687  -0.0978   0.1222   1.0000
  16.000   1.5271   0.09927   0.09141  -0.0981   0.1142   1.0000
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