Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)
Reynolds number: 1,000,000
Max Cl/Cd: 146 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ste87391-il-1000000.txt
Download as CSV file: xf-ste87391-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 87(-3)-914 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
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.4228   0.08170   0.07933  -0.1294   0.9491   0.0096
 -15.000  -0.4591   0.07106   0.06852  -0.1364   0.9479   0.0095
 -14.750  -0.4846   0.06246   0.05977  -0.1428   0.9464   0.0094
 -14.500  -0.5039   0.05511   0.05225  -0.1487   0.9448   0.0094
 -14.250  -0.5180   0.04874   0.04571  -0.1541   0.9431   0.0095
 -14.000  -0.5271   0.04345   0.04025  -0.1587   0.9414   0.0095
 -13.750  -0.5329   0.03911   0.03573  -0.1624   0.9399   0.0096
 -13.500  -0.5355   0.03566   0.03212  -0.1650   0.9384   0.0097
 -13.250  -0.5348   0.03289   0.02917  -0.1670   0.9369   0.0099
 -13.000  -0.5302   0.03070   0.02684  -0.1683   0.9350   0.0101
 -12.750  -0.5227   0.02899   0.02499  -0.1692   0.9332   0.0102
 -12.500  -0.5126   0.02771   0.02357  -0.1697   0.9316   0.0103
 -12.250  -0.5125   0.02502   0.02071  -0.1694   0.9298   0.0107
 -12.000  -0.4999   0.02376   0.01938  -0.1694   0.9285   0.0109
 -11.750  -0.4866   0.02296   0.01852  -0.1691   0.9274   0.0111
 -11.500  -0.4699   0.02226   0.01775  -0.1692   0.9263   0.0114
 -11.250  -0.4513   0.02170   0.01713  -0.1693   0.9252   0.0117
 -11.000  -0.4335   0.02114   0.01651  -0.1689   0.9238   0.0121
 -10.750  -0.4154   0.02059   0.01587  -0.1684   0.9221   0.0125
 -10.500  -0.3968   0.02007   0.01526  -0.1678   0.9207   0.0128
 -10.250  -0.3770   0.01962   0.01471  -0.1672   0.9194   0.0130
 -10.000  -0.3576   0.01892   0.01392  -0.1666   0.9183   0.0132
  -9.750  -0.3407   0.01777   0.01274  -0.1659   0.9172   0.0136
  -9.500  -0.3191   0.01717   0.01212  -0.1656   0.9164   0.0139
  -9.250  -0.2955   0.01664   0.01155  -0.1656   0.9157   0.0143
  -9.000  -0.2707   0.01614   0.01101  -0.1657   0.9150   0.0148
  -8.750  -0.2460   0.01570   0.01052  -0.1657   0.9143   0.0152
  -8.500  -0.2212   0.01542   0.01019  -0.1656   0.9136   0.0157
  -8.250  -0.2336   0.01592   0.01068  -0.1581   0.9075   0.0158
  -8.000  -0.2144   0.01537   0.01009  -0.1571   0.9060   0.0164
  -7.750  -0.1892   0.01487   0.00957  -0.1572   0.9050   0.0170
  -7.500  -0.1619   0.01446   0.00913  -0.1576   0.9043   0.0175
  -7.250  -0.1344   0.01411   0.00874  -0.1579   0.9037   0.0180
  -7.000  -0.1054   0.01378   0.00837  -0.1585   0.9032   0.0186
  -6.750  -0.0754   0.01345   0.00800  -0.1593   0.9027   0.0191
  -6.500  -0.0455   0.01297   0.00750  -0.1602   0.9023   0.0201
  -6.250  -0.0670   0.01364   0.00816  -0.1505   0.8939   0.0203
  -6.000  -0.0377   0.01338   0.00788  -0.1511   0.8929   0.0214
  -5.750  -0.0055   0.01307   0.00755  -0.1522   0.8924   0.0229
  -5.500   0.0273   0.01276   0.00724  -0.1535   0.8920   0.0250
  -5.250   0.0612   0.01243   0.00692  -0.1550   0.8917   0.0296
  -5.000   0.0969   0.01140   0.00640  -0.1577   0.8914   0.1378
  -4.750   0.1305   0.01107   0.00621  -0.1592   0.8910   0.1740
  -4.500   0.1643   0.01083   0.00602  -0.1606   0.8905   0.1908
  -4.250   0.1982   0.01063   0.00583  -0.1620   0.8901   0.2030
  -4.000   0.2322   0.01039   0.00564  -0.1634   0.8897   0.2171
  -3.750   0.2670   0.01014   0.00543  -0.1651   0.8893   0.2309
  -3.500   0.3029   0.00987   0.00518  -0.1668   0.8888   0.2433
  -3.250   0.3397   0.00956   0.00490  -0.1688   0.8883   0.2574
  -3.000   0.3776   0.00919   0.00459  -0.1710   0.8876   0.2782
  -2.750   0.4091   0.00895   0.00442  -0.1720   0.8856   0.3021
  -2.250   0.4621   0.00845   0.00411  -0.1717   0.8790   0.3594
  -2.000   0.4989   0.00797   0.00374  -0.1737   0.8770   0.4020
  -1.750   0.5390   0.00743   0.00333  -0.1764   0.8750   0.4561
  -1.500   0.5776   0.00698   0.00305  -0.1789   0.8730   0.5238
  -1.250   0.6026   0.00676   0.00304  -0.1786   0.8698   0.5930
  -1.000   0.6287   0.00656   0.00307  -0.1784   0.8662   0.6667
  -0.750   0.6585   0.00645   0.00303  -0.1788   0.8633   0.7038
  -0.500   0.6904   0.00634   0.00294  -0.1796   0.8607   0.7208
  -0.250   0.7233   0.00625   0.00284  -0.1806   0.8582   0.7321
   0.000   0.7442   0.00631   0.00292  -0.1792   0.8536   0.7410
   0.250   0.7696   0.00628   0.00288  -0.1787   0.8485   0.7476
   0.500   0.7991   0.00618   0.00280  -0.1790   0.8443   0.7531
   0.750   0.8200   0.00622   0.00287  -0.1775   0.8378   0.7582
   1.000   0.8442   0.00620   0.00283  -0.1767   0.8300   0.7632
   1.250   0.8625   0.00623   0.00285  -0.1747   0.8186   0.7672
   1.500   0.8849   0.00619   0.00280  -0.1735   0.8032   0.7715
   1.750   0.9081   0.00622   0.00273  -0.1724   0.7781   0.7748
   2.000   0.9255   0.00649   0.00281  -0.1702   0.7418   0.7782
   2.250   0.9370   0.00697   0.00308  -0.1668   0.7015   0.7819
   2.500   0.9462   0.00752   0.00344  -0.1631   0.6628   0.7851
   2.750   0.9564   0.00806   0.00380  -0.1597   0.6269   0.7882
   3.000   0.9669   0.00858   0.00420  -0.1563   0.5929   0.7927
   3.500   0.9909   0.00973   0.00507  -0.1503   0.5266   0.8059
   3.750   1.0035   0.01023   0.00546  -0.1474   0.4953   0.8124
   4.000   1.0191   0.01072   0.00583  -0.1452   0.4651   0.8168
   4.250   1.0357   0.01120   0.00618  -0.1434   0.4372   0.8192
   4.500   1.0541   0.01163   0.00649  -0.1419   0.4124   0.8209
   4.750   1.0731   0.01204   0.00681  -0.1405   0.3891   0.8221
   5.000   1.0925   0.01246   0.00712  -0.1393   0.3671   0.8232
   5.250   1.1120   0.01286   0.00744  -0.1380   0.3465   0.8243
   5.500   1.1318   0.01323   0.00773  -0.1369   0.3281   0.8259
   5.750   1.1516   0.01361   0.00804  -0.1357   0.3122   0.8271
   6.000   1.1710   0.01401   0.00838  -0.1345   0.2974   0.8282
   6.250   1.1914   0.01437   0.00871  -0.1335   0.2846   0.8293
   6.500   1.2116   0.01474   0.00904  -0.1324   0.2718   0.8304
   6.750   1.2310   0.01515   0.00940  -0.1313   0.2590   0.8316
   7.250   1.2701   0.01596   0.01013  -0.1290   0.2358   0.8345
   7.500   1.2892   0.01639   0.01053  -0.1278   0.2249   0.8357
   7.750   1.3075   0.01688   0.01095  -0.1265   0.2114   0.8369
   8.000   1.3267   0.01732   0.01134  -0.1254   0.2002   0.8381
   8.250   1.3463   0.01773   0.01174  -0.1244   0.1908   0.8393
   8.500   1.3646   0.01822   0.01219  -0.1231   0.1808   0.8404
   8.750   1.3823   0.01874   0.01267  -0.1218   0.1704   0.8414
   9.000   1.3995   0.01929   0.01316  -0.1204   0.1578   0.8426
   9.250   1.4158   0.01987   0.01370  -0.1190   0.1439   0.8442
   9.500   1.4291   0.02064   0.01435  -0.1170   0.1230   0.8457
   9.750   1.4348   0.02188   0.01537  -0.1140   0.0892   0.8472
  10.000   1.4376   0.02334   0.01661  -0.1105   0.0571   0.8488
  10.250   1.4402   0.02486   0.01794  -0.1071   0.0287   0.8503
  10.500   1.4435   0.02635   0.01932  -0.1039   0.0112   0.8522
  10.750   1.4552   0.02732   0.02030  -0.1020   0.0086   0.8541
  11.000   1.4678   0.02823   0.02125  -0.1002   0.0076   0.8559
  11.250   1.4792   0.02922   0.02231  -0.0982   0.0070   0.8575
  11.500   1.4913   0.03019   0.02333  -0.0965   0.0066   0.8589
  11.750   1.5026   0.03120   0.02441  -0.0947   0.0062   0.8612
  12.000   1.5115   0.03240   0.02568  -0.0927   0.0058   0.8634
  12.250   1.5171   0.03388   0.02726  -0.0903   0.0055   0.8656
  12.500   1.5245   0.03525   0.02871  -0.0882   0.0053   0.8680
  12.750   1.5325   0.03660   0.03014  -0.0863   0.0052   0.8705
  13.000   1.5397   0.03806   0.03168  -0.0844   0.0050   0.8731
  13.250   1.5462   0.03961   0.03331  -0.0826   0.0049   0.8757
  13.500   1.5516   0.04126   0.03506  -0.0808   0.0048   0.8791
  13.750   1.5559   0.04304   0.03694  -0.0789   0.0046   0.8828
  14.000   1.5594   0.04498   0.03896  -0.0772   0.0045   0.8869
  14.250   1.5622   0.04704   0.04112  -0.0756   0.0044   0.8914
  14.500   1.5634   0.04929   0.04348  -0.0739   0.0043   0.8975
  14.750   1.5632   0.05175   0.04606  -0.0724   0.0043   0.9053
  15.000   1.5605   0.05442   0.04887  -0.0708   0.0042   0.9190
  15.250   1.5547   0.05711   0.05173  -0.0689   0.0042   0.9981
  15.500   1.5507   0.06040   0.05512  -0.0680   0.0041   0.9981
  15.750   1.5445   0.06406   0.05889  -0.0672   0.0041   0.9981
  16.000   1.5366   0.06803   0.06297  -0.0667   0.0041   0.9981
  16.250   1.5280   0.07222   0.06727  -0.0665   0.0040   0.9981
  16.500   1.5180   0.07674   0.07190  -0.0666   0.0040   0.9981
  16.750   1.5070   0.08152   0.07680  -0.0669   0.0040   0.9981
  17.000   1.4934   0.08681   0.08221  -0.0676   0.0040   0.9981
  17.250   1.4803   0.09212   0.08765  -0.0685   0.0039   0.9981
<< Back to EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)