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EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il)
Reynolds number: 500,000
Max Cl/Cd: 92.24 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stf86361-il-500000.txt
Download as CSV file: xf-stf86361-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1372   0.08740   0.08464  -0.1413   0.9285   0.0135
 -11.500  -0.1368   0.08236   0.07962  -0.1446   0.9271   0.0137
 -11.250  -0.1380   0.07636   0.07364  -0.1490   0.9257   0.0139
 -11.000  -0.1421   0.06916   0.06643  -0.1552   0.9241   0.0139
 -10.750  -0.1512   0.06325   0.06047  -0.1601   0.9225   0.0138
 -10.500  -0.1630   0.05833   0.05545  -0.1636   0.9209   0.0138
 -10.250  -0.1756   0.05404   0.05103  -0.1660   0.9188   0.0139
 -10.000  -0.1906   0.05059   0.04743  -0.1670   0.9157   0.0140
  -9.750  -0.2093   0.04831   0.04493  -0.1660   0.9121   0.0141
  -9.500  -0.2227   0.04616   0.04246  -0.1640   0.9094   0.0142
  -9.250  -0.2287   0.04408   0.04004  -0.1622   0.9075   0.0142
  -8.750  -0.2995   0.04684   0.04296  -0.1391   0.8955   0.0142
  -8.500  -0.3036   0.04481   0.04055  -0.1363   0.8937   0.0142
  -8.250  -0.2879   0.04089   0.03674  -0.1366   0.8932   0.0144
  -8.000  -0.3544   0.04468   0.04037  -0.1184   0.8839   0.0143
  -7.750  -0.3409   0.04137   0.03716  -0.1180   0.8824   0.0145
  -7.500  -0.3266   0.03922   0.03493  -0.1177   0.8811   0.0147
  -7.250  -0.3076   0.03707   0.03261  -0.1180   0.8800   0.0152
  -7.000  -0.2816   0.03527   0.03005  -0.1181   0.8790   0.0171
  -6.750  -0.2554   0.03182   0.02654  -0.1194   0.8786   0.0177
  -6.500  -0.2258   0.03004   0.02462  -0.1208   0.8781   0.0193
  -6.250  -0.1925   0.02824   0.02229  -0.1225   0.8776   0.0238
  -6.000  -0.1614   0.02664   0.02065  -0.1241   0.8773   0.0276
  -5.000  -0.0333   0.02268   0.01606  -0.1267   0.8761   0.0236
  -4.750  -0.0619   0.02352   0.01689  -0.1168   0.8659   0.0236
  -4.500  -0.0310   0.02288   0.01623  -0.1175   0.8650   0.0235
  -4.250   0.0019   0.02188   0.01537  -0.1193   0.8643   0.0245
  -4.000   0.0358   0.02141   0.01489  -0.1211   0.8637   0.0261
  -3.750   0.0709   0.02098   0.01443  -0.1232   0.8631   0.0266
  -3.500   0.1089   0.02043   0.01388  -0.1260   0.8626   0.0275
  -3.250   0.1465   0.02003   0.01347  -0.1285   0.8622   0.0292
  -3.000   0.1839   0.01971   0.01312  -0.1309   0.8617   0.0313
  -2.750   0.2205   0.01947   0.01283  -0.1330   0.8613   0.0338
  -2.500   0.2822   0.01755   0.01282  -0.1434   0.8617   0.6166
  -2.250   0.3133   0.01781   0.01311  -0.1437   0.8611   0.6412
  -2.000   0.3071   0.01880   0.01412  -0.1375   0.8510   0.6494
  -1.750   0.3341   0.01901   0.01433  -0.1371   0.8492   0.6607
  -1.500   0.3633   0.01922   0.01453  -0.1370   0.8479   0.6719
  -1.250   0.3911   0.01932   0.01472  -0.1364   0.8469   0.6813
  -1.000   0.4226   0.01934   0.01474  -0.1370   0.8461   0.6884
  -0.750   0.4543   0.01930   0.01471  -0.1376   0.8456   0.6953
  -0.500   0.4814   0.01936   0.01485  -0.1370   0.8449   0.7019
  -0.250   0.5151   0.01920   0.01468  -0.1384   0.8444   0.7040
   0.000   0.5498   0.01899   0.01445  -0.1401   0.8439   0.7050
   0.250   0.5422   0.02006   0.01552  -0.1344   0.8320   0.7063
   0.500   0.5756   0.01990   0.01536  -0.1359   0.8312   0.7074
   0.750   0.6100   0.01968   0.01515  -0.1375   0.8306   0.7083
   1.000   0.6449   0.01943   0.01492  -0.1393   0.8300   0.7088
   1.250   0.6804   0.01911   0.01461  -0.1411   0.8294   0.7094
   1.500   0.7172   0.01868   0.01421  -0.1430   0.8290   0.7100
   1.750   0.7553   0.01814   0.01370  -0.1452   0.8286   0.7107
   2.000   0.7930   0.01759   0.01320  -0.1473   0.8284   0.7113
   2.250   0.8299   0.01712   0.01278  -0.1494   0.8281   0.7119
   2.500   0.8654   0.01660   0.01233  -0.1511   0.8266   0.7124
   2.750   0.9515   0.01393   0.00972  -0.1619   0.8272   0.7128
   3.000   0.9412   0.01407   0.00992  -0.1542   0.8153   0.7135
   3.250   0.9939   0.01227   0.00816  -0.1585   0.8084   0.7140
   3.500   1.0022   0.01191   0.00784  -0.1543   0.7918   0.7147
   3.750   1.0048   0.01204   0.00800  -0.1493   0.7651   0.7157
   4.000   1.0349   0.01122   0.00656  -0.1488   0.6531   0.7165
   4.250   1.0182   0.01266   0.00751  -0.1404   0.5693   0.7171
   4.500   1.0014   0.01433   0.00871  -0.1325   0.4763   0.7178
   4.750   0.9911   0.01599   0.00989  -0.1263   0.3890   0.7183
   5.000   0.9798   0.01793   0.01113  -0.1201   0.2604   0.7189
   5.250   0.9717   0.01994   0.01234  -0.1148   0.1189   0.7194
   5.500   0.9723   0.02157   0.01345  -0.1108   0.0310   0.7200
   5.750   0.9888   0.02224   0.01411  -0.1093   0.0246   0.7206
   6.000   1.0060   0.02287   0.01477  -0.1080   0.0218   0.7212
   6.250   1.0214   0.02364   0.01556  -0.1065   0.0202   0.7218
   6.500   1.0379   0.02432   0.01631  -0.1050   0.0192   0.7224
   6.750   1.0528   0.02512   0.01716  -0.1034   0.0182   0.7230
   7.000   1.0638   0.02620   0.01825  -0.1012   0.0174   0.7236
   7.250   1.0774   0.02711   0.01923  -0.0994   0.0168   0.7244
   7.500   1.0914   0.02798   0.02016  -0.0978   0.0157   0.7253
   7.750   1.1016   0.02916   0.02134  -0.0956   0.0148   0.7261
   8.000   1.1125   0.03036   0.02261  -0.0935   0.0143   0.7267
   8.250   1.1271   0.03132   0.02366  -0.0918   0.0138   0.7273
   8.500   1.1419   0.03234   0.02475  -0.0903   0.0132   0.7278
   8.750   1.1578   0.03340   0.02584  -0.0889   0.0126   0.7283
   9.000   1.1845   0.03480   0.02722  -0.0887   0.0119   0.7288
   9.250   1.2016   0.03584   0.02849  -0.0872   0.0114   0.7293
   9.500   1.2192   0.03688   0.02968  -0.0861   0.0106   0.7301
   9.750   1.2394   0.03790   0.03067  -0.0857   0.0099   0.7310
  10.000   1.2661   0.03981   0.03281  -0.0857   0.0094   0.7318
  10.250   1.2820   0.04163   0.03494  -0.0841   0.0091   0.7326
  10.500   1.2954   0.04387   0.03752  -0.0821   0.0088   0.7334
  10.750   1.3036   0.04647   0.04046  -0.0797   0.0085   0.7341
  11.000   1.3060   0.04887   0.04312  -0.0768   0.0081   0.7349
  11.250   1.3069   0.05094   0.04536  -0.0741   0.0079   0.7357
  11.500   1.3157   0.05188   0.04621  -0.0729   0.0075   0.7366
  12.000   1.2913   0.06009   0.05504  -0.0652   0.0072   0.7379
  12.250   1.2717   0.06376   0.05905  -0.0610   0.0071   0.7385
  12.500   1.2540   0.06799   0.06353  -0.0576   0.0072   0.7391
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