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S1210 12% (s1210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.88 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1210-il-1000000-n5.txt
Download as CSV file: xf-s1210-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1210 12%                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0647   0.09807   0.09628  -0.0822   0.9526   0.0064
  -9.000  -0.0492   0.09101   0.08922  -0.0858   0.9389   0.0067
  -8.500  -0.1668   0.03998   0.03773  -0.1321   0.9056   0.0078
  -8.250  -0.0834   0.02406   0.02118  -0.1770   0.8828   0.0079
  -8.000   0.0132   0.01820   0.01478  -0.2035   0.8583   0.0081
  -7.750   0.0680   0.01661   0.01283  -0.2123   0.8244   0.0083
  -7.500   0.1079   0.01553   0.01142  -0.2168   0.7896   0.0084
  -7.250   0.1437   0.01470   0.01030  -0.2198   0.7582   0.0086
  -7.000   0.1786   0.01403   0.00939  -0.2223   0.7296   0.0088
  -6.750   0.2130   0.01352   0.00866  -0.2244   0.7039   0.0090
  -6.500   0.2486   0.01300   0.00790  -0.2267   0.6798   0.0093
  -6.250   0.2851   0.01247   0.00717  -0.2291   0.6581   0.0095
  -6.000   0.3204   0.01204   0.00656  -0.2311   0.6383   0.0097
  -5.750   0.3550   0.01170   0.00606  -0.2328   0.6216   0.0099
  -5.500   0.3889   0.01142   0.00565  -0.2343   0.6075   0.0101
  -5.250   0.4221   0.01121   0.00531  -0.2356   0.5944   0.0102
  -5.000   0.4613   0.01069   0.00466  -0.2385   0.5821   0.0107
  -4.750   0.4959   0.01043   0.00431  -0.2401   0.5715   0.0110
  -4.500   0.5292   0.01026   0.00405  -0.2413   0.5614   0.0113
  -4.250   0.5623   0.01010   0.00380  -0.2425   0.5520   0.0116
  -4.000   0.5949   0.00997   0.00359  -0.2435   0.5435   0.0119
  -3.750   0.6273   0.00985   0.00340  -0.2444   0.5350   0.0122
  -3.500   0.6588   0.00978   0.00325  -0.2451   0.5270   0.0128
  -3.250   0.6900   0.00972   0.00313  -0.2457   0.5189   0.0132
  -3.000   0.7219   0.00965   0.00297  -0.2465   0.5117   0.0138
  -2.750   0.7533   0.00958   0.00285  -0.2472   0.5055   0.0147
  -2.500   0.7839   0.00957   0.00278  -0.2476   0.4991   0.0158
  -2.250   0.8142   0.00956   0.00273  -0.2480   0.4939   0.0172
  -2.000   0.8460   0.00948   0.00267  -0.2488   0.4885   0.0329
  -1.750   0.8836   0.00918   0.00258  -0.2512   0.4825   0.1311
  -1.500   0.9173   0.00904   0.00263  -0.2525   0.4775   0.2190
  -1.250   0.9465   0.00909   0.00268  -0.2527   0.4725   0.2370
  -1.000   0.9754   0.00915   0.00274  -0.2528   0.4677   0.2454
  -0.750   1.0037   0.00924   0.00278  -0.2527   0.4635   0.2507
  -0.500   1.0326   0.00929   0.00283  -0.2528   0.4599   0.2564
  -0.250   1.0613   0.00936   0.00289  -0.2528   0.4557   0.2624
   0.000   1.0896   0.00945   0.00295  -0.2527   0.4515   0.2658
   0.250   1.1177   0.00955   0.00302  -0.2526   0.4475   0.2685
   0.500   1.1464   0.00961   0.00308  -0.2526   0.4445   0.2721
   0.750   1.1748   0.00969   0.00316  -0.2526   0.4403   0.2762
   1.000   1.2027   0.00980   0.00325  -0.2525   0.4349   0.2803
   1.250   1.2305   0.00992   0.00334  -0.2524   0.4292   0.2841
   1.500   1.2586   0.01001   0.00343  -0.2523   0.4238   0.2886
   1.750   1.2865   0.01012   0.00353  -0.2522   0.4193   0.2942
   2.000   1.3141   0.01025   0.00365  -0.2520   0.4153   0.2998
   2.250   1.3421   0.01033   0.00375  -0.2520   0.4120   0.3057
   2.500   1.3699   0.01043   0.00387  -0.2519   0.4063   0.3136
   2.750   1.3970   0.01060   0.00401  -0.2516   0.3995   0.3215
   3.000   1.4248   0.01069   0.00414  -0.2515   0.3949   0.3310
   3.250   1.4520   0.01084   0.00428  -0.2513   0.3873   0.3397
   3.500   1.4791   0.01100   0.00443  -0.2511   0.3796   0.3502
   3.750   1.5062   0.01115   0.00459  -0.2509   0.3711   0.3612
   4.000   1.5331   0.01132   0.00476  -0.2506   0.3636   0.3730
   4.250   1.5599   0.01148   0.00493  -0.2504   0.3553   0.3861
   4.500   1.5864   0.01169   0.00514  -0.2501   0.3444   0.4004
   4.750   1.6119   0.01199   0.00538  -0.2496   0.3264   0.4155
   5.000   1.6365   0.01240   0.00570  -0.2490   0.3049   0.4339
   5.500   1.6846   0.01332   0.00647  -0.2477   0.2621   0.4735
   5.750   1.7082   0.01380   0.00688  -0.2469   0.2433   0.4943
   6.000   1.7319   0.01425   0.00729  -0.2462   0.2271   0.5167
   6.250   1.7556   0.01470   0.00772  -0.2454   0.2130   0.5412
   6.500   1.7790   0.01515   0.00815  -0.2446   0.1998   0.5679
   6.750   1.8026   0.01558   0.00859  -0.2439   0.1876   0.5995
   7.000   1.8262   0.01602   0.00905  -0.2432   0.1761   0.6400
   7.250   1.8492   0.01649   0.00955  -0.2423   0.1647   0.6837
   7.500   1.8714   0.01702   0.01010  -0.2413   0.1528   0.7326
   7.750   1.8931   0.01757   0.01070  -0.2403   0.1416   0.7992
   8.000   1.9066   0.01782   0.01113  -0.2373   0.1350   1.0000
   8.250   1.9244   0.01841   0.01169  -0.2354   0.1273   1.0000
   8.500   1.9418   0.01897   0.01223  -0.2335   0.1200   1.0000
   8.750   1.9576   0.01962   0.01286  -0.2313   0.1125   1.0000
   9.000   1.9741   0.02023   0.01346  -0.2292   0.1066   1.0000
   9.250   1.9902   0.02089   0.01411  -0.2271   0.1015   1.0000
   9.500   2.0069   0.02148   0.01473  -0.2251   0.0979   1.0000
   9.750   2.0208   0.02226   0.01550  -0.2227   0.0923   1.0000
  10.000   2.0354   0.02301   0.01627  -0.2204   0.0877   1.0000
  10.250   2.0501   0.02374   0.01703  -0.2183   0.0846   1.0000
  10.500   2.0628   0.02462   0.01791  -0.2158   0.0809   1.0000
  10.750   2.0749   0.02556   0.01887  -0.2133   0.0772   1.0000
  11.000   2.0884   0.02639   0.01975  -0.2110   0.0749   1.0000
  11.250   2.1003   0.02735   0.02075  -0.2086   0.0725   1.0000
  11.500   2.1070   0.02872   0.02211  -0.2056   0.0667   1.0000
  11.750   2.1164   0.02991   0.02333  -0.2030   0.0626   1.0000
  12.000   2.1214   0.03148   0.02490  -0.2000   0.0576   1.0000
  12.250   2.1274   0.03303   0.02648  -0.1973   0.0530   1.0000
  12.500   2.1316   0.03478   0.02826  -0.1945   0.0489   1.0000
  12.750   2.1320   0.03696   0.03045  -0.1916   0.0428   1.0000
  13.000   2.1258   0.03989   0.03338  -0.1883   0.0348   1.0000
  13.250   2.1181   0.04319   0.03670  -0.1854   0.0281   1.0000
  13.500   2.1140   0.04632   0.03988  -0.1832   0.0243   1.0000
  13.750   2.1031   0.05048   0.04409  -0.1810   0.0185   1.0000
  14.000   2.0891   0.05535   0.04901  -0.1793   0.0132   1.0000
  14.250   2.0839   0.05929   0.05304  -0.1783   0.0112   1.0000
  14.500   2.0743   0.06406   0.05789  -0.1775   0.0085   1.0000
  14.750   2.0616   0.06946   0.06338  -0.1771   0.0058   1.0000
  15.000   2.0462   0.07548   0.06950  -0.1770   0.0029   1.0000
  15.250   2.0414   0.07999   0.07411  -0.1770   0.0026   1.0000
  15.500   2.0285   0.08592   0.08015  -0.1774   0.0016   1.0000
  15.750   2.0223   0.09079   0.08512  -0.1778   0.0015   1.0000
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