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S1223 (s1223-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S1223 (s1223-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.38 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1223-il-1000000.txt
Download as CSV file: xf-s1223-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1223                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000   0.1302   0.09491   0.09315  -0.1002   0.9451   0.0111
  -7.750   0.1438   0.09210   0.09034  -0.1022   0.9414   0.0115
  -7.500   0.1477   0.08930   0.08755  -0.1025   0.9339   0.0125
  -7.250   0.1547   0.08588   0.08413  -0.1053   0.9280   0.0126
  -6.750   0.1784   0.08025   0.07848  -0.1085   0.9065   0.0127
  -6.500   0.2218   0.07527   0.07343  -0.1173   0.8916   0.0129
  -6.250   0.3142   0.06875   0.06644  -0.1393   0.8206   0.0133
  -6.000   0.3098   0.06818   0.06542  -0.1357   0.7309   0.0134
  -5.750   0.3021   0.06766   0.06458  -0.1314   0.6598   0.0136
  -5.500   0.3003   0.06669   0.06343  -0.1289   0.6172   0.0138
  -5.250   0.2976   0.06552   0.06216  -0.1263   0.5889   0.0139
  -5.000   0.2945   0.06443   0.06099  -0.1237   0.5651   0.0142
  -4.750   0.2976   0.06264   0.05914  -0.1228   0.5474   0.0146
  -4.500   0.3027   0.06059   0.05706  -0.1225   0.5335   0.0148
  -4.250   0.3087   0.05827   0.05472  -0.1230   0.5221   0.0151
  -4.000   0.3200   0.05435   0.05077  -0.1271   0.5126   0.0155
  -3.750   0.3372   0.05082   0.04721  -0.1312   0.5036   0.0156
  -3.500   0.3597   0.04733   0.04368  -0.1362   0.4939   0.0156
  -3.250   0.3917   0.04220   0.03850  -0.1455   0.4854   0.0159
  -3.000   0.4257   0.03943   0.03567  -0.1519   0.4762   0.0161
  -2.750   0.4777   0.03536   0.03149  -0.1636   0.4665   0.0165
  -2.500   0.8683   0.01239   0.00596  -0.2633   0.4429   0.0170
  -2.250   0.9015   0.01231   0.00578  -0.2643   0.4348   0.0182
  -2.000   0.9399   0.01206   0.00540  -0.2665   0.4273   0.0194
  -1.750   0.9755   0.01191   0.00521  -0.2681   0.4212   0.0206
  -1.500   1.0088   0.01188   0.00510  -0.2692   0.4146   0.0218
  -1.250   1.0443   0.01180   0.00493  -0.2707   0.4086   0.0232
  -1.000   1.0771   0.01176   0.00487  -0.2716   0.4039   0.0252
  -0.750   1.1089   0.01178   0.00482  -0.2723   0.3985   0.0268
  -0.500   1.1410   0.01184   0.00479  -0.2731   0.3923   0.0289
  -0.250   1.1720   0.01185   0.00479  -0.2735   0.3890   0.0316
   0.000   1.2030   0.01188   0.00481  -0.2740   0.3854   0.0384
   0.250   1.2438   0.01171   0.00495  -0.2770   0.3813   0.1927
   0.500   1.2720   0.01186   0.00509  -0.2769   0.3771   0.2184
   1.000   1.3277   0.01212   0.00536  -0.2765   0.3708   0.2532
   1.250   1.3557   0.01223   0.00549  -0.2764   0.3684   0.2701
   1.500   1.3832   0.01236   0.00562  -0.2762   0.3658   0.2819
   1.750   1.4104   0.01251   0.00576  -0.2759   0.3631   0.2952
   2.000   1.4378   0.01267   0.00594  -0.2756   0.3603   0.3114
   2.250   1.4647   0.01289   0.00614  -0.2753   0.3568   0.3258
   2.500   1.4918   0.01306   0.00632  -0.2750   0.3545   0.3430
   2.750   1.5193   0.01317   0.00649  -0.2748   0.3529   0.3631
   3.000   1.5466   0.01330   0.00666  -0.2746   0.3512   0.3864
   3.500   1.6009   0.01361   0.00706  -0.2741   0.3474   0.4445
   3.750   1.6278   0.01379   0.00730  -0.2738   0.3453   0.4781
   4.000   1.6544   0.01399   0.00755  -0.2735   0.3431   0.5149
   4.250   1.6808   0.01425   0.00784  -0.2731   0.3401   0.5571
   4.500   1.7073   0.01453   0.00818  -0.2728   0.3374   0.6064
   4.750   1.7353   0.01465   0.00844  -0.2728   0.3363   0.6683
   5.000   1.7636   0.01477   0.00871  -0.2728   0.3347   0.7527
   5.250   1.7831   0.01469   0.00890  -0.2709   0.3328   1.0000
   5.500   1.8080   0.01490   0.00911  -0.2703   0.3307   1.0000
   5.750   1.8325   0.01513   0.00934  -0.2695   0.3283   1.0000
   6.000   1.8564   0.01541   0.00959  -0.2687   0.3254   1.0000
   6.250   1.8795   0.01578   0.00993  -0.2677   0.3219   1.0000
   6.500   1.9033   0.01607   0.01023  -0.2668   0.3197   1.0000
   6.750   1.9278   0.01626   0.01046  -0.2661   0.3184   1.0000
   7.000   1.9519   0.01647   0.01070  -0.2654   0.3167   1.0000
   7.250   1.9757   0.01669   0.01095  -0.2645   0.3143   1.0000
   7.500   1.9988   0.01695   0.01122  -0.2636   0.3114   1.0000
   7.750   2.0210   0.01727   0.01153  -0.2624   0.3083   1.0000
   8.000   2.0420   0.01770   0.01194  -0.2611   0.3047   1.0000
   8.250   2.0648   0.01797   0.01225  -0.2601   0.3021   1.0000
   8.500   2.0883   0.01815   0.01248  -0.2593   0.2989   1.0000
   8.750   2.1108   0.01843   0.01277  -0.2583   0.2947   1.0000
   9.000   2.1319   0.01880   0.01314  -0.2571   0.2908   1.0000
   9.250   2.1521   0.01925   0.01359  -0.2557   0.2869   1.0000
   9.500   2.1743   0.01952   0.01392  -0.2546   0.2844   1.0000
   9.750   2.1956   0.01985   0.01429  -0.2535   0.2809   1.0000
  10.000   2.2157   0.02026   0.01472  -0.2521   0.2767   1.0000
  10.250   2.2343   0.02080   0.01525  -0.2505   0.2718   1.0000
  10.500   2.2555   0.02114   0.01565  -0.2493   0.2675   1.0000
  10.750   2.2741   0.02165   0.01616  -0.2478   0.2613   1.0000
  11.000   2.2915   0.02225   0.01676  -0.2460   0.2555   1.0000
  11.250   2.3097   0.02279   0.01733  -0.2444   0.2489   1.0000
  11.500   2.3251   0.02354   0.01806  -0.2424   0.2411   1.0000
  11.750   2.3408   0.02426   0.01879  -0.2404   0.2329   1.0000
  12.000   2.3544   0.02515   0.01967  -0.2381   0.2239   1.0000
  12.250   2.3653   0.02625   0.02074  -0.2355   0.2131   1.0000
  12.500   2.3751   0.02745   0.02190  -0.2328   0.2008   1.0000
  12.750   2.3832   0.02877   0.02319  -0.2298   0.1892   1.0000
  13.000   2.3902   0.03021   0.02461  -0.2268   0.1785   1.0000
  13.250   2.3946   0.03185   0.02623  -0.2235   0.1684   1.0000
  13.500   2.3974   0.03366   0.02803  -0.2202   0.1588   1.0000
  13.750   2.4021   0.03535   0.02974  -0.2172   0.1504   1.0000
  14.000   2.4033   0.03739   0.03178  -0.2140   0.1423   1.0000
  14.250   2.4030   0.03963   0.03404  -0.2108   0.1345   1.0000
  14.500   2.4036   0.04186   0.03630  -0.2079   0.1280   1.0000
  14.750   2.3985   0.04474   0.03919  -0.2047   0.1206   1.0000
  15.000   2.3954   0.04753   0.04202  -0.2020   0.1136   1.0000
  15.250   2.3861   0.05116   0.04568  -0.1992   0.1064   1.0000
  15.500   2.3777   0.05487   0.04944  -0.1968   0.1005   1.0000
  15.750   2.3681   0.05893   0.05356  -0.1948   0.0961   1.0000
  16.000   2.3598   0.06302   0.05775  -0.1933   0.0925   1.0000
  16.250   2.3438   0.06842   0.06323  -0.1921   0.0883   1.0000
  16.500   2.3291   0.07393   0.06885  -0.1915   0.0852   1.0000
  16.750   2.3126   0.07996   0.07499  -0.1913   0.0821   1.0000
  17.000   2.2895   0.08728   0.08244  -0.1917   0.0791   1.0000
  17.250   2.2657   0.09493   0.09023  -0.1926   0.0770   1.0000
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