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CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: CH10 (smoothed) (ch10sm-il)
Reynolds number: 200,000
Max Cl/Cd: 86.22 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ch10sm-il-200000-n5.txt
Download as CSV file: xf-ch10sm-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.2241   0.11034   0.10559  -0.1540   0.8300   0.0228
 -10.750   0.2313   0.10813   0.10338  -0.1554   0.8258   0.0229
 -10.500   0.2386   0.10582   0.10107  -0.1567   0.8212   0.0229
 -10.250   0.2514   0.10258   0.09781  -0.1567   0.8175   0.0232
 -10.000   0.2622   0.10013   0.09532  -0.1574   0.8141   0.0236
  -9.750   0.2718   0.09791   0.09310  -0.1582   0.8098   0.0240
  -9.500   0.2811   0.09572   0.09090  -0.1591   0.8053   0.0246
  -9.250   0.2906   0.09347   0.08862  -0.1601   0.8015   0.0252
  -9.000   0.3005   0.09116   0.08627  -0.1614   0.7983   0.0260
  -8.750   0.3084   0.08899   0.08413  -0.1627   0.7937   0.0270
  -8.500   0.3143   0.08702   0.08216  -0.1646   0.7891   0.0274
  -8.250   0.3174   0.08534   0.08047  -0.1673   0.7849   0.0276
  -8.000   0.3357   0.08207   0.07715  -0.1660   0.7824   0.0284
  -7.750   0.3455   0.08017   0.07528  -0.1663   0.7780   0.0293
  -7.500   0.3549   0.07815   0.07326  -0.1671   0.7739   0.0301
  -7.250   0.3645   0.07604   0.07113  -0.1682   0.7702   0.0309
  -7.000   0.3740   0.07389   0.06894  -0.1695   0.7669   0.0319
  -6.750   0.3774   0.07220   0.06730  -0.1707   0.7619   0.0327
  -6.500   0.3826   0.07042   0.06554  -0.1728   0.7576   0.0330
  -6.250   0.3953   0.06791   0.06301  -0.1763   0.7542   0.0331
  -6.000   0.4101   0.06524   0.06031  -0.1795   0.7509   0.0331
  -5.750   0.4227   0.06278   0.05787  -0.1816   0.7465   0.0331
  -5.500   0.4403   0.05984   0.05491  -0.1860   0.7425   0.0332
  -5.250   0.4476   0.05932   0.05440  -0.1798   0.7398   0.0355
  -4.750   0.4924   0.05086   0.04584  -0.1936   0.7327   0.0273
  -4.500   0.5147   0.04817   0.04312  -0.1976   0.7288   0.0269
  -4.250   0.5478   0.04436   0.03924  -0.2052   0.7255   0.0267
  -3.750   0.7185   0.02413   0.01774  -0.2536   0.7211   0.0288
  -3.500   0.7581   0.02172   0.01487  -0.2583   0.7175   0.0300
  -3.250   0.7957   0.01996   0.01254  -0.2616   0.7141   0.0327
  -3.000   0.8285   0.01901   0.01133  -0.2634   0.7109   0.0342
  -2.750   0.8604   0.01845   0.01058  -0.2647   0.7082   0.0358
  -2.500   0.8938   0.01783   0.00971  -0.2662   0.7059   0.0380
  -2.250   0.9197   0.01751   0.00929  -0.2662   0.7021   0.0410
  -2.000   0.9465   0.01736   0.00911  -0.2664   0.6984   0.0441
  -1.750   0.9757   0.01706   0.00867  -0.2669   0.6953   0.0477
  -1.500   1.0057   0.01685   0.00842  -0.2676   0.6927   0.0524
  -1.250   1.0359   0.01670   0.00816  -0.2683   0.6902   0.0579
  -1.000   1.0603   0.01665   0.00815  -0.2680   0.6862   0.0638
  -0.750   1.0865   0.01662   0.00807  -0.2680   0.6827   0.0702
  -0.500   1.1148   0.01652   0.00798  -0.2684   0.6796   0.0787
  -0.250   1.1445   0.01644   0.00784  -0.2690   0.6770   0.0885
   0.000   1.1729   0.01643   0.00779  -0.2694   0.6742   0.1014
   0.250   1.1966   0.01649   0.00793  -0.2690   0.6702   0.1201
   0.500   1.2227   0.01650   0.00804  -0.2690   0.6668   0.1591
   0.750   1.2505   0.01644   0.00816  -0.2694   0.6638   0.2453
   1.000   1.2799   0.01639   0.00824  -0.2701   0.6611   0.3364
   1.250   1.3051   0.01647   0.00847  -0.2699   0.6578   0.4133
   1.500   1.3279   0.01662   0.00878  -0.2693   0.6539   0.4855
   1.750   1.3529   0.01671   0.00899  -0.2690   0.6505   0.5614
   2.000   1.3790   0.01662   0.00913  -0.2689   0.6475   0.6943
   2.250   1.4021   0.01635   0.00904  -0.2679   0.6449   1.0000
   2.500   1.4215   0.01670   0.00938  -0.2666   0.6408   1.0000
   2.750   1.4433   0.01698   0.00963  -0.2657   0.6368   1.0000
   3.000   1.4675   0.01719   0.00979  -0.2653   0.6334   1.0000
   3.250   1.4951   0.01734   0.00985  -0.2655   0.6305   1.0000
   3.500   1.5166   0.01764   0.01014  -0.2646   0.6269   1.0000
   3.750   1.5345   0.01800   0.01052  -0.2631   0.6226   1.0000
   4.000   1.5553   0.01827   0.01078  -0.2621   0.6188   1.0000
   4.250   1.5810   0.01845   0.01090  -0.2619   0.6158   1.0000
   4.500   1.6023   0.01874   0.01118  -0.2610   0.6122   1.0000
   4.750   1.6153   0.01921   0.01170  -0.2586   0.6075   1.0000
   5.000   1.6341   0.01954   0.01206  -0.2573   0.6035   1.0000
   5.250   1.6591   0.01973   0.01221  -0.2570   0.6002   1.0000
   5.500   1.6757   0.02015   0.01266  -0.2553   0.5961   1.0000
   5.750   1.6869   0.02072   0.01330  -0.2527   0.5911   1.0000
   6.000   1.7057   0.02108   0.01368  -0.2514   0.5869   1.0000
   6.250   1.7322   0.02121   0.01377  -0.2515   0.5836   1.0000
   6.500   1.7364   0.02208   0.01475  -0.2478   0.5779   1.0000
   6.750   1.7501   0.02264   0.01536  -0.2458   0.5730   1.0000
   7.000   1.7734   0.02286   0.01557  -0.2453   0.5692   1.0000
   7.250   1.7806   0.02373   0.01654  -0.2424   0.5636   1.0000
   7.500   1.7911   0.02448   0.01736  -0.2400   0.5582   1.0000
   7.750   1.8126   0.02477   0.01764  -0.2392   0.5540   1.0000
   8.000   1.8182   0.02581   0.01880  -0.2362   0.5481   1.0000
   8.250   1.8281   0.02667   0.01973  -0.2339   0.5424   1.0000
   8.500   1.8498   0.02693   0.01998  -0.2332   0.5380   1.0000
   8.750   1.8489   0.02845   0.02163  -0.2295   0.5310   1.0000
   9.000   1.8618   0.02920   0.02243  -0.2277   0.5253   1.0000
   9.250   1.8733   0.03007   0.02337  -0.2257   0.5197   1.0000
   9.500   1.8766   0.03148   0.02489  -0.2228   0.5128   1.0000
   9.750   1.8941   0.03197   0.02539  -0.2216   0.5076   1.0000
  10.000   1.8926   0.03378   0.02734  -0.2183   0.5003   1.0000
  10.250   1.9040   0.03470   0.02832  -0.2165   0.4941   1.0000
  10.500   1.9085   0.03618   0.02990  -0.2139   0.4873   1.0000
  10.750   1.9146   0.03755   0.03134  -0.2116   0.4803   1.0000
  11.000   1.9225   0.03881   0.03267  -0.2096   0.4736   1.0000
  11.250   1.9249   0.04057   0.03453  -0.2071   0.4659   1.0000
  11.500   1.9336   0.04181   0.03584  -0.2052   0.4590   1.0000
  11.750   1.9334   0.04384   0.03796  -0.2025   0.4494   1.0000
  12.000   1.9313   0.04609   0.04026  -0.1998   0.4383   1.0000
  12.250   1.9288   0.04838   0.04258  -0.1971   0.4251   1.0000
  12.500   1.9238   0.05099   0.04519  -0.1943   0.4099   1.0000
  12.750   1.9176   0.05381   0.04800  -0.1915   0.3937   1.0000
  13.000   1.9107   0.05678   0.05094  -0.1888   0.3767   1.0000
  13.250   1.9030   0.05990   0.05404  -0.1862   0.3595   1.0000
  13.500   1.8948   0.06316   0.05726  -0.1837   0.3424   1.0000
  13.750   1.8857   0.06658   0.06065  -0.1812   0.3254   1.0000
  14.000   1.8760   0.07019   0.06422  -0.1789   0.3080   1.0000
  14.250   1.8654   0.07394   0.06795  -0.1767   0.2900   1.0000
  14.500   1.8530   0.07798   0.07194  -0.1746   0.2713   1.0000
  14.750   1.8392   0.08230   0.07620  -0.1726   0.2523   1.0000
  15.000   1.8260   0.08662   0.08047  -0.1708   0.2339   1.0000
  15.250   1.8134   0.09093   0.08474  -0.1691   0.2151   1.0000
  15.500   1.7997   0.09545   0.08921  -0.1677   0.1959   1.0000
  15.750   1.7849   0.10018   0.09388  -0.1664   0.1755   1.0000
  16.000   1.7677   0.10534   0.09893  -0.1652   0.1525   1.0000
  16.250   1.7496   0.11069   0.10417  -0.1644   0.1276   1.0000
  16.500   1.7307   0.11616   0.10951  -0.1637   0.1029   1.0000
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