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S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S9026 (9.5%) (s9026-il)
Reynolds number: 200,000
Max Cl/Cd: 45.3 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9026-il-200000-n5.txt
Download as CSV file: xf-s9026-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9026 (9.5%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8923   0.09710   0.09331   0.0025   1.0000   0.0186
 -13.750  -0.9447   0.08097   0.07700  -0.0082   1.0000   0.0178
 -13.500  -0.9836   0.06893   0.06472  -0.0168   1.0000   0.0172
 -13.250  -1.0044   0.06132   0.05691  -0.0223   1.0000   0.0172
 -13.000  -1.0220   0.05506   0.05044  -0.0266   1.0000   0.0173
 -12.750  -1.0358   0.05012   0.04529  -0.0294   1.0000   0.0174
 -12.500  -1.0458   0.04634   0.04131  -0.0307   1.0000   0.0178
 -12.250  -1.0554   0.04301   0.03776  -0.0309   1.0000   0.0181
 -12.000  -1.0610   0.04048   0.03502  -0.0299   1.0000   0.0186
 -11.750  -1.0652   0.03823   0.03253  -0.0281   1.0000   0.0191
 -11.500  -1.0659   0.03627   0.03033  -0.0258   1.0000   0.0195
 -11.250  -1.0604   0.03448   0.02825  -0.0240   1.0000   0.0200
 -11.000  -1.0543   0.03246   0.02612  -0.0224   1.0000   0.0208
 -10.750  -1.0425   0.03113   0.02471  -0.0211   1.0000   0.0217
 -10.500  -1.0279   0.03002   0.02349  -0.0200   1.0000   0.0227
 -10.250  -1.0128   0.02874   0.02205  -0.0188   1.0000   0.0237
 -10.000  -0.9965   0.02744   0.02057  -0.0176   1.0000   0.0247
  -9.750  -0.9788   0.02628   0.01921  -0.0165   1.0000   0.0258
  -9.500  -0.9609   0.02507   0.01784  -0.0154   1.0000   0.0270
  -9.250  -0.9437   0.02382   0.01651  -0.0142   1.0000   0.0283
  -9.000  -0.9243   0.02286   0.01547  -0.0133   1.0000   0.0296
  -8.750  -0.9042   0.02195   0.01445  -0.0123   1.0000   0.0311
  -8.500  -0.8835   0.02108   0.01346  -0.0113   1.0000   0.0329
  -8.250  -0.8617   0.02036   0.01260  -0.0104   1.0000   0.0348
  -8.000  -0.8421   0.01938   0.01162  -0.0094   1.0000   0.0377
  -7.750  -0.8202   0.01869   0.01085  -0.0086   1.0000   0.0408
  -7.500  -0.7979   0.01804   0.01008  -0.0077   1.0000   0.0441
  -7.250  -0.7765   0.01728   0.00931  -0.0067   1.0000   0.0482
  -7.000  -0.7538   0.01672   0.00870  -0.0059   1.0000   0.0534
  -6.750  -0.7312   0.01614   0.00810  -0.0051   1.0000   0.0595
  -6.500  -0.7081   0.01566   0.00757  -0.0043   1.0000   0.0668
  -6.250  -0.6854   0.01514   0.00706  -0.0034   1.0000   0.0744
  -6.000  -0.6623   0.01470   0.00661  -0.0026   1.0000   0.0834
  -5.500  -0.6164   0.01384   0.00579  -0.0009   1.0000   0.1077
  -5.250  -0.5937   0.01342   0.00541   0.0000   1.0000   0.1227
  -5.000  -0.5710   0.01301   0.00507   0.0009   1.0000   0.1389
  -4.750  -0.5482   0.01264   0.00476   0.0018   1.0000   0.1559
  -4.500  -0.5254   0.01229   0.00447   0.0027   1.0000   0.1754
  -4.250  -0.5028   0.01195   0.00419   0.0036   1.0000   0.1973
  -4.000  -0.4801   0.01164   0.00396   0.0046   1.0000   0.2202
  -3.750  -0.4576   0.01134   0.00375   0.0055   1.0000   0.2442
  -3.500  -0.4354   0.01104   0.00357   0.0065   1.0000   0.2720
  -3.250  -0.4136   0.01076   0.00341   0.0076   1.0000   0.3039
  -3.000  -0.3841   0.01047   0.00328   0.0070   0.9963   0.3415
  -2.750  -0.3474   0.01019   0.00316   0.0050   0.9882   0.3830
  -2.500  -0.3107   0.00994   0.00305   0.0030   0.9797   0.4236
  -2.250  -0.2744   0.00968   0.00295   0.0012   0.9699   0.4652
  -2.000  -0.2408   0.00943   0.00287   0.0001   0.9572   0.5067
  -1.750  -0.2074   0.00919   0.00280  -0.0009   0.9440   0.5500
  -1.500  -0.1742   0.00897   0.00275  -0.0018   0.9298   0.5926
  -1.250  -0.1409   0.00879   0.00270  -0.0025   0.9135   0.6320
  -1.000  -0.1094   0.00864   0.00266  -0.0028   0.8938   0.6678
  -0.750  -0.0799   0.00852   0.00263  -0.0026   0.8711   0.7025
  -0.500  -0.0522   0.00843   0.00261  -0.0020   0.8472   0.7361
  -0.250  -0.0258   0.00838   0.00259  -0.0010   0.8223   0.7673
   0.000   0.0000   0.00837   0.00259   0.0000   0.7958   0.7958
   0.250   0.0258   0.00838   0.00259   0.0010   0.7673   0.8222
   0.500   0.0522   0.00843   0.00261   0.0020   0.7360   0.8471
   0.750   0.0799   0.00852   0.00263   0.0026   0.7025   0.8711
   1.000   0.1094   0.00864   0.00266   0.0028   0.6678   0.8938
   1.250   0.1409   0.00879   0.00270   0.0025   0.6320   0.9134
   1.500   0.1742   0.00897   0.00275   0.0018   0.5928   0.9298
   1.750   0.2075   0.00919   0.00280   0.0009   0.5502   0.9440
   2.000   0.2409   0.00943   0.00287  -0.0001   0.5066   0.9572
   2.250   0.2744   0.00968   0.00296  -0.0012   0.4651   0.9699
   2.500   0.3108   0.00994   0.00305  -0.0030   0.4237   0.9796
   2.750   0.3474   0.01020   0.00316  -0.0050   0.3829   0.9881
   3.000   0.3841   0.01047   0.00328  -0.0070   0.3416   0.9962
   3.250   0.4137   0.01076   0.00341  -0.0076   0.3037   1.0000
   3.500   0.4356   0.01104   0.00357  -0.0066   0.2720   1.0000
   3.750   0.4578   0.01134   0.00375  -0.0056   0.2441   1.0000
   4.000   0.4802   0.01164   0.00396  -0.0046   0.2202   1.0000
   4.250   0.5029   0.01195   0.00420  -0.0037   0.1972   1.0000
   4.500   0.5255   0.01229   0.00447  -0.0027   0.1755   1.0000
   4.750   0.5483   0.01264   0.00476  -0.0018   0.1557   1.0000
   5.000   0.5712   0.01301   0.00507  -0.0009   0.1389   1.0000
   5.250   0.5938   0.01342   0.00541   0.0000   0.1226   1.0000
   5.500   0.6165   0.01384   0.00579   0.0009   0.1076   1.0000
   6.000   0.6624   0.01470   0.00661   0.0026   0.0835   1.0000
   6.250   0.6855   0.01514   0.00706   0.0034   0.0744   1.0000
   6.500   0.7082   0.01566   0.00757   0.0043   0.0668   1.0000
   6.750   0.7312   0.01614   0.00811   0.0051   0.0596   1.0000
   7.000   0.7538   0.01672   0.00870   0.0059   0.0534   1.0000
   7.250   0.7764   0.01729   0.00932   0.0067   0.0481   1.0000
   7.500   0.7978   0.01804   0.01009   0.0077   0.0440   1.0000
   7.750   0.8201   0.01869   0.01085   0.0086   0.0408   1.0000
   8.000   0.8420   0.01937   0.01161   0.0094   0.0376   1.0000
   8.250   0.8617   0.02034   0.01258   0.0105   0.0348   1.0000
   8.500   0.8833   0.02108   0.01347   0.0114   0.0329   1.0000
   8.750   0.9039   0.02195   0.01446   0.0123   0.0311   1.0000
   9.000   0.9241   0.02285   0.01546   0.0133   0.0296   1.0000
   9.250   0.9435   0.02381   0.01650   0.0143   0.0283   1.0000
   9.500   0.9606   0.02507   0.01784   0.0154   0.0269   1.0000
   9.750   0.9784   0.02629   0.01923   0.0166   0.0259   1.0000
  10.000   0.9962   0.02744   0.02057   0.0176   0.0247   1.0000
  10.250   1.0124   0.02875   0.02206   0.0188   0.0237   1.0000
  10.500   1.0277   0.03001   0.02347   0.0200   0.0227   1.0000
  10.750   1.0421   0.03115   0.02473   0.0212   0.0217   1.0000
  11.000   1.0542   0.03241   0.02607   0.0224   0.0208   1.0000
  11.250   1.0600   0.03449   0.02826   0.0241   0.0200   1.0000
  11.500   1.0656   0.03625   0.03032   0.0259   0.0195   1.0000
  11.750   1.0649   0.03821   0.03251   0.0282   0.0190   1.0000
  12.000   1.0610   0.04046   0.03500   0.0300   0.0186   1.0000
  12.250   1.0541   0.04319   0.03795   0.0309   0.0182   1.0000
  12.500   1.0453   0.04640   0.04138   0.0307   0.0179   1.0000
  12.750   1.0348   0.05029   0.04547   0.0293   0.0175   1.0000
  13.000   1.0210   0.05526   0.05064   0.0265   0.0174   1.0000
  13.250   1.0039   0.06146   0.05705   0.0222   0.0173   1.0000
  13.500   0.9775   0.07017   0.06599   0.0159   0.0175   1.0000
  13.750   0.9455   0.08089   0.07693   0.0082   0.0178   1.0000
  14.000   0.8925   0.09718   0.09338  -0.0026   0.0186   1.0000
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