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CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: CH10 (smoothed) (ch10sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 175.24 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ch10sm-il-1000000.txt
Download as CSV file: xf-ch10sm-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CH10 (smoothed)                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.3003   0.08978   0.08699  -0.1577   0.7760   0.0121
 -11.000   0.3046   0.08703   0.08422  -0.1587   0.7724   0.0122
 -10.750   0.3103   0.08429   0.08145  -0.1597   0.7687   0.0122
 -10.500   0.3170   0.08159   0.07874  -0.1606   0.7655   0.0122
 -10.250   0.3263   0.07863   0.07579  -0.1608   0.7621   0.0124
 -10.000   0.3354   0.07637   0.07351  -0.1614   0.7585   0.0126
  -9.750   0.3447   0.07419   0.07130  -0.1621   0.7550   0.0128
  -9.500   0.3532   0.07199   0.06908  -0.1627   0.7514   0.0131
  -9.250   0.3617   0.06961   0.06671  -0.1635   0.7482   0.0134
  -9.000   0.3697   0.06716   0.06426  -0.1643   0.7447   0.0138
  -8.750   0.3770   0.06461   0.06170  -0.1650   0.7413   0.0144
  -8.250   0.3430   0.07802   0.07498  -0.1688   0.7490   0.0139
  -8.000   0.3535   0.07563   0.07260  -0.1702   0.7452   0.0146
  -7.750   0.3597   0.07234   0.06930  -0.1733   0.7413   0.0153
  -7.500   0.3686   0.06970   0.06663  -0.1751   0.7373   0.0153
  -7.250   0.3780   0.06698   0.06393  -0.1758   0.7342   0.0156
  -7.000   0.3910   0.06534   0.06230  -0.1764   0.7307   0.0158
  -6.750   0.4029   0.06368   0.06062  -0.1773   0.7270   0.0162
  -6.500   0.4133   0.06202   0.05895  -0.1782   0.7232   0.0166
  -6.250   0.4279   0.05990   0.05682  -0.1805   0.7199   0.0173
  -6.000   0.4475   0.05570   0.05263  -0.1882   0.7165   0.0188
  -5.500   0.5975   0.01576   0.01155  -0.2662   0.7098   0.0187
  -5.250   0.6373   0.01291   0.00810  -0.2714   0.7064   0.0194
  -5.000   0.6678   0.01220   0.00726  -0.2727   0.7037   0.0199
  -4.750   0.6975   0.01173   0.00670  -0.2735   0.7007   0.0204
  -4.500   0.7270   0.01128   0.00614  -0.2743   0.6975   0.0210
  -4.250   0.7562   0.01090   0.00562  -0.2749   0.6943   0.0216
  -4.000   0.7851   0.01063   0.00522  -0.2754   0.6909   0.0224
  -3.750   0.8142   0.01031   0.00482  -0.2760   0.6883   0.0231
  -3.500   0.8439   0.00986   0.00430  -0.2767   0.6853   0.0243
  -3.250   0.8724   0.00969   0.00410  -0.2771   0.6821   0.0252
  -3.000   0.9007   0.00956   0.00390  -0.2774   0.6790   0.0264
  -2.750   0.9290   0.00950   0.00375  -0.2777   0.6757   0.0275
  -2.500   0.9583   0.00923   0.00347  -0.2782   0.6731   0.0297
  -2.250   0.9865   0.00917   0.00341  -0.2785   0.6701   0.0320
  -2.000   1.0151   0.00905   0.00325  -0.2789   0.6670   0.0352
  -1.750   1.0429   0.00904   0.00322  -0.2791   0.6639   0.0386
  -1.500   1.0709   0.00901   0.00314  -0.2793   0.6606   0.0429
  -1.250   1.0987   0.00899   0.00313  -0.2795   0.6579   0.0471
  -1.000   1.1268   0.00892   0.00308  -0.2798   0.6549   0.0525
  -0.750   1.1541   0.00893   0.00308  -0.2799   0.6517   0.0574
  -0.500   1.1815   0.00892   0.00305  -0.2800   0.6486   0.0645
  -0.250   1.2083   0.00900   0.00309  -0.2800   0.6451   0.0706
   0.000   1.2360   0.00896   0.00309  -0.2802   0.6424   0.0822
   0.250   1.2635   0.00894   0.00310  -0.2804   0.6393   0.0975
   0.500   1.2908   0.00891   0.00314  -0.2806   0.6361   0.1311
   0.750   1.3180   0.00886   0.00324  -0.2808   0.6328   0.2161
   1.000   1.3449   0.00890   0.00336  -0.2810   0.6292   0.2867
   1.250   1.3720   0.00886   0.00347  -0.2812   0.6265   0.3520
   1.500   1.3989   0.00886   0.00358  -0.2813   0.6233   0.4108
   1.750   1.4251   0.00890   0.00370  -0.2812   0.6199   0.4685
   2.000   1.4507   0.00897   0.00384  -0.2811   0.6165   0.5254
   2.250   1.4766   0.00904   0.00399  -0.2810   0.6131   0.5873
   2.500   1.5028   0.00901   0.00414  -0.2810   0.6100   0.6679
   2.750   1.5263   0.00871   0.00430  -0.2804   0.6066   1.0000
   3.000   1.5509   0.00886   0.00440  -0.2800   0.6030   1.0000
   3.250   1.5748   0.00906   0.00454  -0.2795   0.5991   1.0000
   3.500   1.5993   0.00915   0.00466  -0.2791   0.5959   1.0000
   3.750   1.6231   0.00927   0.00478  -0.2786   0.5922   1.0000
   4.000   1.6460   0.00944   0.00492  -0.2779   0.5883   1.0000
   4.250   1.6676   0.00966   0.00510  -0.2769   0.5841   1.0000
   4.500   1.6907   0.00980   0.00526  -0.2763   0.5805   1.0000
   4.750   1.7133   0.00995   0.00543  -0.2756   0.5765   1.0000
   5.000   1.7345   0.01016   0.00562  -0.2746   0.5723   1.0000
   5.250   1.7544   0.01043   0.00587  -0.2733   0.5679   1.0000
   5.500   1.7768   0.01059   0.00606  -0.2726   0.5641   1.0000
   5.750   1.7976   0.01081   0.00629  -0.2716   0.5596   1.0000
   6.000   1.8160   0.01112   0.00658  -0.2701   0.5549   1.0000
   6.250   1.8361   0.01138   0.00686  -0.2690   0.5505   1.0000
   6.500   1.8565   0.01163   0.00714  -0.2680   0.5459   1.0000
   6.750   1.8744   0.01198   0.00748  -0.2666   0.5411   1.0000
   7.000   1.8922   0.01235   0.00786  -0.2651   0.5365   1.0000
   7.250   1.9122   0.01264   0.00819  -0.2641   0.5318   1.0000
   7.500   1.9296   0.01303   0.00860  -0.2626   0.5267   1.0000
   7.750   1.9450   0.01354   0.00910  -0.2608   0.5217   1.0000
   8.000   1.9643   0.01388   0.00949  -0.2598   0.5168   1.0000
   8.250   1.9803   0.01438   0.01001  -0.2581   0.5112   1.0000
   8.500   1.9945   0.01497   0.01061  -0.2562   0.5058   1.0000
   8.750   2.0112   0.01547   0.01115  -0.2548   0.4990   1.0000
   9.000   2.0205   0.01633   0.01199  -0.2522   0.4888   1.0000
   9.500   2.0377   0.01825   0.01389  -0.2470   0.4655   1.0000
   9.750   2.0459   0.01929   0.01493  -0.2444   0.4545   1.0000
  10.000   2.0499   0.02061   0.01622  -0.2413   0.4412   1.0000
  10.250   2.0524   0.02209   0.01766  -0.2381   0.4268   1.0000
  10.500   2.0542   0.02367   0.01921  -0.2348   0.4123   1.0000
  10.750   2.0542   0.02542   0.02093  -0.2315   0.3970   1.0000
  11.000   2.0519   0.02743   0.02288  -0.2280   0.3800   1.0000
  11.250   2.0469   0.02972   0.02511  -0.2242   0.3613   1.0000
  11.500   2.0390   0.03230   0.02761  -0.2203   0.3422   1.0000
  11.750   2.0305   0.03502   0.03026  -0.2165   0.3235   1.0000
  12.000   2.0210   0.03794   0.03310  -0.2128   0.3025   1.0000
  12.250   2.0105   0.04102   0.03610  -0.2091   0.2830   1.0000
  12.500   1.9991   0.04426   0.03927  -0.2055   0.2640   1.0000
  12.750   1.9895   0.04743   0.04238  -0.2022   0.2450   1.0000
  13.000   1.9780   0.05085   0.04572  -0.1989   0.2256   1.0000
  13.250   1.9649   0.05448   0.04926  -0.1957   0.2065   1.0000
  13.500   1.9516   0.05824   0.05293  -0.1926   0.1849   1.0000
  13.750   1.9354   0.06239   0.05697  -0.1894   0.1631   1.0000
  14.000   1.9167   0.06687   0.06133  -0.1862   0.1395   1.0000
  14.250   1.8970   0.07159   0.06593  -0.1832   0.1151   1.0000
  14.500   1.8768   0.07650   0.07072  -0.1804   0.0915   1.0000
  14.750   1.8586   0.08125   0.07538  -0.1780   0.0711   1.0000
  15.000   1.8438   0.08572   0.07978  -0.1759   0.0552   1.0000
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