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EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.14 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stf86361-il-1000000.txt
Download as CSV file: xf-stf86361-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STF 863-615 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1653   0.08701   0.08474  -0.1330   0.8935   0.0086
 -11.750  -0.1636   0.08188   0.07960  -0.1362   0.8924   0.0087
 -11.500  -0.1628   0.07581   0.07354  -0.1403   0.8911   0.0087
 -11.250  -0.1661   0.06710   0.06480  -0.1476   0.8904   0.0087
 -11.000  -0.1760   0.06087   0.05850  -0.1529   0.8894   0.0087
 -10.750  -0.1868   0.05597   0.05351  -0.1566   0.8882   0.0087
 -10.500  -0.1970   0.05181   0.04925  -0.1592   0.8869   0.0087
 -10.250  -0.2057   0.04811   0.04543  -0.1612   0.8854   0.0087
 -10.000  -0.2128   0.04483   0.04202  -0.1628   0.8837   0.0087
  -9.750  -0.2134   0.04158   0.03857  -0.1645   0.8821   0.0087
  -9.500  -0.2093   0.03845   0.03522  -0.1653   0.8809   0.0087
  -9.250  -0.2010   0.03547   0.03201  -0.1658   0.8799   0.0087
  -9.000  -0.1973   0.03045   0.02673  -0.1663   0.8787   0.0089
  -8.750  -0.1808   0.02818   0.02431  -0.1668   0.8779   0.0090
  -8.500  -0.1623   0.02614   0.02209  -0.1671   0.8770   0.0091
  -8.250  -0.1435   0.02340   0.01908  -0.1669   0.8759   0.0081
  -8.000  -0.1243   0.01991   0.01518  -0.1662   0.8754   0.0077
  -7.750  -0.1008   0.01813   0.01309  -0.1659   0.8750   0.0092
  -7.500  -0.0755   0.01785   0.01282  -0.1665   0.8747   0.0099
  -7.250  -0.0503   0.01689   0.01170  -0.1664   0.8742   0.0106
  -7.000  -0.0251   0.01586   0.01053  -0.1661   0.8737   0.0109
  -6.750   0.0002   0.01510   0.00965  -0.1659   0.8730   0.0112
  -6.500   0.0245   0.01440   0.00896  -0.1658   0.8724   0.0121
  -6.250   0.0498   0.01401   0.00854  -0.1659   0.8718   0.0132
  -6.000   0.0751   0.01354   0.00797  -0.1656   0.8712   0.0140
  -5.750   0.0978   0.01283   0.00731  -0.1651   0.8705   0.0151
  -5.500   0.1225   0.01248   0.00696  -0.1651   0.8699   0.0160
  -5.250   0.1477   0.01217   0.00662  -0.1651   0.8691   0.0167
  -5.000   0.1726   0.01172   0.00617  -0.1652   0.8682   0.0177
  -4.750   0.1984   0.01136   0.00583  -0.1656   0.8674   0.0190
  -4.500   0.2251   0.01111   0.00556  -0.1659   0.8668   0.0198
  -4.250   0.2522   0.01094   0.00537  -0.1663   0.8661   0.0203
  -4.000   0.2797   0.01057   0.00500  -0.1670   0.8654   0.0211
  -3.750   0.3081   0.01037   0.00479  -0.1677   0.8647   0.0222
  -3.500   0.3370   0.01022   0.00463  -0.1685   0.8639   0.0233
  -3.250   0.3664   0.01005   0.00444  -0.1693   0.8632   0.0245
  -3.000   0.3970   0.00992   0.00430  -0.1703   0.8621   0.0262
  -2.750   0.4271   0.00990   0.00425  -0.1712   0.8606   0.0296
  -2.500   0.4604   0.00798   0.00402  -0.1752   0.8592   0.6151
  -2.250   0.4871   0.00823   0.00429  -0.1751   0.8581   0.6346
  -2.000   0.5130   0.00846   0.00457  -0.1748   0.8571   0.6442
  -1.750   0.5393   0.00871   0.00484  -0.1746   0.8558   0.6517
  -1.500   0.5661   0.00883   0.00497  -0.1746   0.8543   0.6572
  -1.250   0.5929   0.00891   0.00508  -0.1746   0.8526   0.6612
  -1.000   0.6204   0.00902   0.00522  -0.1746   0.8511   0.6653
  -0.750   0.6489   0.00911   0.00532  -0.1750   0.8497   0.6693
  -0.500   0.6787   0.00908   0.00528  -0.1757   0.8486   0.6702
  -0.250   0.7088   0.00905   0.00525  -0.1766   0.8476   0.6709
   0.000   0.7392   0.00903   0.00524  -0.1776   0.8466   0.6713
   0.250   0.7707   0.00899   0.00520  -0.1787   0.8454   0.6718
   0.500   0.8003   0.00908   0.00529  -0.1795   0.8433   0.6724
   0.750   0.8257   0.00903   0.00527  -0.1793   0.8416   0.6729
   1.000   0.8509   0.00901   0.00528  -0.1791   0.8393   0.6732
   1.250   0.8777   0.00891   0.00523  -0.1792   0.8365   0.6735
   1.500   0.9119   0.00845   0.00476  -0.1807   0.8321   0.6742
   1.750   0.9484   0.00810   0.00437  -0.1827   0.8272   0.6749
   2.000   0.9687   0.00784   0.00417  -0.1813   0.8208   0.6756
   2.250   0.9994   0.00741   0.00373  -0.1820   0.8116   0.6763
   2.500   1.0142   0.00715   0.00349  -0.1791   0.7950   0.6771
   2.750   1.0232   0.00705   0.00335  -0.1751   0.7612   0.6779
   3.000   1.0102   0.00766   0.00355  -0.1664   0.6840   0.6785
   3.250   0.9950   0.00889   0.00438  -0.1578   0.6059   0.6791
   3.500   0.9843   0.01012   0.00526  -0.1506   0.5359   0.6797
   3.750   0.9738   0.01156   0.00625  -0.1437   0.4440   0.6802
   4.000   0.9721   0.01279   0.00709  -0.1387   0.3606   0.6808
   4.250   0.9654   0.01439   0.00810  -0.1330   0.2448   0.6813
   4.500   0.9622   0.01596   0.00907  -0.1281   0.1287   0.6818
   4.750   0.9636   0.01740   0.01000  -0.1239   0.0306   0.6823
   5.000   0.9802   0.01801   0.01055  -0.1224   0.0182   0.6828
   5.250   0.9992   0.01848   0.01104  -0.1213   0.0162   0.6833
   5.500   1.0175   0.01900   0.01159  -0.1200   0.0149   0.6838
   5.750   1.0358   0.01952   0.01214  -0.1188   0.0142   0.6844
   6.000   1.0542   0.02004   0.01270  -0.1177   0.0136   0.6849
   6.250   1.0716   0.02062   0.01331  -0.1163   0.0129   0.6855
   6.500   1.0861   0.02141   0.01413  -0.1145   0.0122   0.6862
   6.750   1.1031   0.02201   0.01478  -0.1132   0.0115   0.6869
   7.000   1.1198   0.02264   0.01546  -0.1118   0.0109   0.6876
   7.250   1.1352   0.02334   0.01621  -0.1102   0.0104   0.6881
   7.500   1.1477   0.02425   0.01714  -0.1082   0.0099   0.6886
   7.750   1.1556   0.02550   0.01845  -0.1055   0.0095   0.6891
   8.000   1.1722   0.02616   0.01918  -0.1042   0.0092   0.6896
   8.250   1.1877   0.02690   0.01998  -0.1027   0.0088   0.6901
   8.500   1.2033   0.02763   0.02076  -0.1014   0.0082   0.6905
   8.750   1.2181   0.02839   0.02155  -0.1000   0.0077   0.6910
   9.000   1.2264   0.02971   0.02293  -0.0975   0.0071   0.6913
   9.250   1.2426   0.03042   0.02372  -0.0963   0.0068   0.6917
   9.500   1.2565   0.03134   0.02472  -0.0947   0.0064   0.6921
   9.750   1.2700   0.03228   0.02573  -0.0931   0.0060   0.6925
  10.000   1.2836   0.03320   0.02672  -0.0917   0.0058   0.6935
  10.250   1.2961   0.03421   0.02779  -0.0901   0.0056   0.6944
  10.500   1.3067   0.03543   0.02908  -0.0883   0.0053   0.6952
  10.750   1.3144   0.03738   0.03118  -0.0858   0.0051   0.6959
  11.000   1.3266   0.03841   0.03234  -0.0842   0.0050   0.6968
  11.250   1.3376   0.03965   0.03371  -0.0825   0.0048   0.6975
  11.500   1.3471   0.04102   0.03522  -0.0807   0.0046   0.6983
  11.750   1.3557   0.04249   0.03684  -0.0788   0.0044   0.6991
  12.000   1.3634   0.04402   0.03851  -0.0770   0.0042   0.6998
  12.250   1.3702   0.04550   0.04010  -0.0752   0.0040   0.7006
  12.500   1.3766   0.04698   0.04168  -0.0735   0.0039   0.7014
  12.750   1.3828   0.04849   0.04328  -0.0720   0.0037   0.7022
  13.000   1.3890   0.04998   0.04485  -0.0706   0.0036   0.7031
  13.250   1.3927   0.05185   0.04681  -0.0690   0.0035   0.7039
  13.500   1.3696   0.05703   0.05238  -0.0647   0.0032   0.7043
  13.750   1.3718   0.05917   0.05466  -0.0633   0.0031   0.7051
  14.000   1.3646   0.06255   0.05825  -0.0614   0.0031   0.7058
  14.250   1.3549   0.06638   0.06230  -0.0595   0.0029   0.7066
  14.500   1.3375   0.07132   0.06750  -0.0577   0.0029   0.7072
  14.750   1.3127   0.07752   0.07398  -0.0564   0.0028   0.7076
  15.000   1.2853   0.08451   0.08124  -0.0560   0.0028   0.7080
  15.250   1.2524   0.09291   0.08993  -0.0568   0.0028   0.7083
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