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SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SD7084 (9.6%) (sd7084-il)
Reynolds number: 100,000
Max Cl/Cd: 49.67 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7084-il-100000-n5.txt
Download as CSV file: xf-sd7084-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7084 (9.6%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4358   0.11912   0.11395  -0.0192   1.0000   0.0522
 -10.500  -0.4433   0.11583   0.11075  -0.0238   1.0000   0.0549
 -10.250  -0.4460   0.11213   0.10710  -0.0270   1.0000   0.0552
  -9.500  -0.4441   0.09338   0.08842  -0.0330   1.0000   0.0317
  -9.250  -0.4420   0.08980   0.08488  -0.0332   1.0000   0.0310
  -9.000  -0.4428   0.08582   0.08095  -0.0345   1.0000   0.0306
  -8.750  -0.4453   0.08176   0.07695  -0.0362   1.0000   0.0303
  -8.500  -0.4509   0.07749   0.07276  -0.0382   1.0000   0.0299
  -8.250  -0.4623   0.07295   0.06830  -0.0407   1.0000   0.0296
  -8.000  -0.4736   0.06843   0.06382  -0.0427   1.0000   0.0291
  -7.750  -0.4849   0.06384   0.05921  -0.0436   1.0000   0.0288
  -7.500  -0.4953   0.05956   0.05486  -0.0434   1.0000   0.0285
  -7.250  -0.5046   0.05528   0.05044  -0.0425   1.0000   0.0282
  -7.000  -0.5104   0.05121   0.04618  -0.0411   1.0000   0.0281
  -6.750  -0.5128   0.04720   0.04191  -0.0395   1.0000   0.0280
  -6.500  -0.5112   0.04349   0.03786  -0.0377   1.0000   0.0286
  -6.250  -0.5059   0.04006   0.03402  -0.0359   1.0000   0.0296
  -6.000  -0.4971   0.03692   0.03040  -0.0341   1.0000   0.0305
  -5.750  -0.4854   0.03405   0.02703  -0.0323   1.0000   0.0309
  -5.500  -0.4680   0.03137   0.02388  -0.0313   0.9991   0.0311
  -5.250  -0.4368   0.02870   0.02064  -0.0326   0.9946   0.0315
  -5.000  -0.4060   0.02638   0.01789  -0.0336   0.9901   0.0321
  -4.750  -0.3742   0.02431   0.01558  -0.0348   0.9857   0.0333
  -4.500  -0.3408   0.02311   0.01425  -0.0364   0.9812   0.0358
  -4.250  -0.3085   0.02212   0.01304  -0.0374   0.9756   0.0393
  -4.000  -0.2734   0.02095   0.01170  -0.0388   0.9712   0.0412
  -3.750  -0.2420   0.02001   0.01061  -0.0395   0.9653   0.0431
  -3.500  -0.2094   0.01898   0.00959  -0.0407   0.9596   0.0469
  -3.250  -0.1757   0.01829   0.00880  -0.0419   0.9539   0.0533
  -3.000  -0.1435   0.01759   0.00810  -0.0429   0.9469   0.0697
  -2.750  -0.1077   0.01671   0.00747  -0.0447   0.9418   0.1178
  -2.500  -0.0806   0.01569   0.00716  -0.0451   0.9335   0.2587
  -2.250  -0.0479   0.01463   0.00700  -0.0464   0.9283   0.4750
  -2.000  -0.0231   0.01404   0.00692  -0.0453   0.9191   0.6246
  -1.750   0.0105   0.01358   0.00689  -0.0451   0.9138   0.7745
  -1.500   0.0597   0.01341   0.00683  -0.0481   0.9081   0.8915
  -1.250   0.1240   0.01330   0.00656  -0.0549   0.9046   0.9547
  -1.000   0.1860   0.01314   0.00621  -0.0615   0.9004   0.9873
  -0.750   0.2248   0.01302   0.00594  -0.0638   0.8891   1.0000
  -0.500   0.2507   0.01291   0.00570  -0.0633   0.8754   1.0000
  -0.250   0.2760   0.01281   0.00549  -0.0626   0.8611   1.0000
   0.000   0.3012   0.01271   0.00528  -0.0618   0.8460   1.0000
   0.250   0.3264   0.01262   0.00509  -0.0610   0.8303   1.0000
   0.500   0.3499   0.01257   0.00495  -0.0598   0.8120   1.0000
   0.750   0.3744   0.01251   0.00481  -0.0588   0.7936   1.0000
   1.000   0.3998   0.01246   0.00465  -0.0579   0.7750   1.0000
   1.250   0.4242   0.01245   0.00455  -0.0569   0.7543   1.0000
   1.500   0.4493   0.01246   0.00445  -0.0559   0.7333   1.0000
   1.750   0.4738   0.01251   0.00441  -0.0549   0.7104   1.0000
   2.000   0.4985   0.01259   0.00437  -0.0540   0.6875   1.0000
   2.250   0.5227   0.01272   0.00438  -0.0529   0.6633   1.0000
   2.500   0.5467   0.01288   0.00443  -0.0519   0.6386   1.0000
   2.750   0.5705   0.01306   0.00453  -0.0509   0.6138   1.0000
   3.000   0.5943   0.01328   0.00463  -0.0499   0.5892   1.0000
   3.250   0.6177   0.01352   0.00478  -0.0489   0.5643   1.0000
   3.500   0.6411   0.01379   0.00495  -0.0479   0.5397   1.0000
   3.750   0.6644   0.01408   0.00518  -0.0470   0.5158   1.0000
   4.000   0.6876   0.01439   0.00540  -0.0460   0.4921   1.0000
   4.250   0.7107   0.01471   0.00566  -0.0451   0.4689   1.0000
   4.500   0.7336   0.01507   0.00594  -0.0441   0.4470   1.0000
   4.750   0.7566   0.01542   0.00626  -0.0432   0.4252   1.0000
   5.000   0.7793   0.01582   0.00662  -0.0423   0.4050   1.0000
   5.250   0.8021   0.01620   0.00700  -0.0414   0.3851   1.0000
   5.500   0.8247   0.01662   0.00739  -0.0405   0.3663   1.0000
   5.750   0.8471   0.01707   0.00781  -0.0396   0.3491   1.0000
   6.000   0.8697   0.01751   0.00827  -0.0387   0.3319   1.0000
   6.250   0.8920   0.01797   0.00880  -0.0378   0.3157   1.0000
   6.500   0.9141   0.01845   0.00932  -0.0369   0.3000   1.0000
   6.750   0.9360   0.01895   0.00986  -0.0360   0.2850   1.0000
   7.000   0.9576   0.01948   0.01043  -0.0350   0.2701   1.0000
   7.250   0.9788   0.02002   0.01103  -0.0341   0.2554   1.0000
   7.500   0.9996   0.02058   0.01170  -0.0330   0.2406   1.0000
   7.750   1.0198   0.02116   0.01235  -0.0319   0.2255   1.0000
   8.000   1.0394   0.02176   0.01303  -0.0308   0.2102   1.0000
   8.250   1.0583   0.02239   0.01373  -0.0295   0.1938   1.0000
   8.500   1.0767   0.02303   0.01448  -0.0283   0.1748   1.0000
   8.750   1.0931   0.02377   0.01524  -0.0268   0.1544   1.0000
   9.000   1.1085   0.02462   0.01612  -0.0254   0.1282   1.0000
   9.250   1.1215   0.02573   0.01711  -0.0237   0.0961   1.0000
   9.500   1.1304   0.02724   0.01841  -0.0217   0.0655   1.0000
   9.750   1.1371   0.02892   0.01999  -0.0194   0.0453   1.0000
  10.000   1.1406   0.03067   0.02173  -0.0166   0.0343   1.0000
  10.250   1.1409   0.03248   0.02361  -0.0134   0.0290   1.0000
  10.500   1.1418   0.03424   0.02553  -0.0106   0.0258   1.0000
  10.750   1.1390   0.03634   0.02774  -0.0080   0.0237   1.0000
  11.000   1.1340   0.03870   0.03023  -0.0056   0.0224   1.0000
  11.250   1.1329   0.04092   0.03266  -0.0038   0.0211   1.0000
  11.500   1.1310   0.04335   0.03528  -0.0024   0.0201   1.0000
  11.750   1.1290   0.04594   0.03803  -0.0015   0.0190   1.0000
  12.000   1.1256   0.04882   0.04105  -0.0010   0.0180   1.0000
  12.250   1.1204   0.05208   0.04448  -0.0011   0.0170   1.0000
  12.500   1.1142   0.05571   0.04825  -0.0015   0.0166   1.0000
  12.750   1.1054   0.05988   0.05254  -0.0022   0.0161   1.0000
  13.000   1.1012   0.06371   0.05653  -0.0030   0.0158   1.0000
  13.250   1.0962   0.06785   0.06087  -0.0041   0.0154   1.0000
  13.500   1.0908   0.07218   0.06539  -0.0054   0.0152   1.0000
  13.750   1.0845   0.07681   0.07020  -0.0070   0.0151   1.0000
  14.000   1.0769   0.08183   0.07542  -0.0090   0.0149   1.0000
  14.250   1.0677   0.08737   0.08114  -0.0115   0.0148   1.0000
  14.500   1.0579   0.09322   0.08718  -0.0143   0.0147   1.0000
  14.750   1.0462   0.09969   0.09384  -0.0177   0.0146   1.0000
  15.000   1.0339   0.10656   0.10088  -0.0214   0.0146   1.0000
  15.250   1.0209   0.11386   0.10835  -0.0255   0.0147   1.0000
  15.500   1.0064   0.12186   0.11650  -0.0301   0.0148   1.0000
  15.750   0.9907   0.13055   0.12534  -0.0351   0.0149   1.0000
  16.000   0.9748   0.13976   0.13468  -0.0405   0.0151   1.0000
  16.250   0.9588   0.14953   0.14455  -0.0461   0.0153   1.0000
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