Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S1012 (s1012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S1012 (s1012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.3 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1012-il-1000000-n5.txt
Download as CSV file: xf-s1012-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1012                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.500  -1.1248   0.11570   0.11290  -0.0109   1.0000   0.0101
 -19.250  -1.2051   0.09626   0.09320  -0.0224   1.0000   0.0099
 -19.000  -1.2727   0.07950   0.07615  -0.0325   1.0000   0.0098
 -18.750  -1.3142   0.06812   0.06455  -0.0394   1.0000   0.0097
 -18.500  -1.3339   0.06118   0.05744  -0.0434   1.0000   0.0097
 -18.250  -1.3506   0.05528   0.05138  -0.0464   1.0000   0.0097
 -18.000  -1.3595   0.05096   0.04694  -0.0481   1.0000   0.0098
 -17.750  -1.3680   0.04704   0.04288  -0.0493   1.0000   0.0099
 -17.500  -1.3719   0.04395   0.03969  -0.0497   1.0000   0.0099
 -17.250  -1.3783   0.04087   0.03649  -0.0497   1.0000   0.0102
 -17.000  -1.3807   0.03835   0.03388  -0.0493   1.0000   0.0103
 -16.750  -1.3817   0.03611   0.03155  -0.0486   1.0000   0.0105
 -16.500  -1.3797   0.03422   0.02957  -0.0478   1.0000   0.0106
 -16.250  -1.3762   0.03252   0.02780  -0.0468   1.0000   0.0109
 -16.000  -1.3713   0.03100   0.02620  -0.0457   1.0000   0.0111
 -15.750  -1.3651   0.02962   0.02474  -0.0445   1.0000   0.0113
 -15.500  -1.3572   0.02840   0.02346  -0.0432   1.0000   0.0116
 -15.250  -1.3488   0.02724   0.02224  -0.0419   1.0000   0.0119
 -15.000  -1.3391   0.02620   0.02112  -0.0406   1.0000   0.0122
 -14.750  -1.3285   0.02524   0.02009  -0.0393   1.0000   0.0124
 -14.500  -1.3171   0.02435   0.01913  -0.0379   1.0000   0.0126
 -14.250  -1.3058   0.02347   0.01819  -0.0365   1.0000   0.0127
 -14.000  -1.2951   0.02255   0.01721  -0.0349   1.0000   0.0132
 -13.750  -1.2830   0.02172   0.01634  -0.0334   1.0000   0.0136
 -13.500  -1.2696   0.02099   0.01557  -0.0319   1.0000   0.0140
 -13.000  -1.2240   0.01962   0.01407  -0.0325   0.9444   0.0152
 -12.750  -1.2091   0.01915   0.01345  -0.0308   0.9137   0.0156
 -12.500  -1.1953   0.01869   0.01288  -0.0289   0.8981   0.0159
 -12.250  -1.1814   0.01814   0.01226  -0.0270   0.8876   0.0166
 -12.000  -1.1666   0.01766   0.01170  -0.0252   0.8793   0.0173
 -11.750  -1.1506   0.01719   0.01119  -0.0235   0.8726   0.0181
 -11.500  -1.1342   0.01678   0.01071  -0.0218   0.8663   0.0188
 -11.250  -1.1169   0.01641   0.01028  -0.0202   0.8614   0.0195
 -11.000  -1.0994   0.01600   0.00983  -0.0186   0.8568   0.0204
 -10.750  -1.0802   0.01559   0.00939  -0.0174   0.8528   0.0215
 -10.500  -1.0597   0.01523   0.00899  -0.0163   0.8494   0.0227
 -10.250  -1.0382   0.01489   0.00860  -0.0154   0.8466   0.0237
 -10.000  -1.0167   0.01451   0.00821  -0.0146   0.8438   0.0252
  -9.750  -0.9947   0.01415   0.00784  -0.0137   0.8411   0.0269
  -9.500  -0.9721   0.01384   0.00750  -0.0130   0.8385   0.0285
  -9.250  -0.9491   0.01354   0.00716  -0.0123   0.8361   0.0299
  -9.000  -0.9263   0.01321   0.00683  -0.0116   0.8339   0.0320
  -8.750  -0.9028   0.01293   0.00653  -0.0110   0.8319   0.0339
  -8.500  -0.8785   0.01267   0.00624  -0.0105   0.8302   0.0354
  -8.250  -0.8546   0.01236   0.00594  -0.0100   0.8283   0.0381
  -8.000  -0.8303   0.01209   0.00567  -0.0095   0.8262   0.0406
  -7.750  -0.8054   0.01186   0.00542  -0.0090   0.8243   0.0425
  -7.500  -0.7807   0.01161   0.00516  -0.0086   0.8224   0.0451
  -7.250  -0.7559   0.01136   0.00492  -0.0082   0.8208   0.0480
  -7.000  -0.7306   0.01115   0.00470  -0.0078   0.8193   0.0507
  -6.750  -0.7054   0.01092   0.00447  -0.0074   0.8178   0.0544
  -6.500  -0.6801   0.01070   0.00426  -0.0070   0.8163   0.0585
  -6.250  -0.6539   0.01052   0.00407  -0.0068   0.8151   0.0614
  -6.000  -0.6283   0.01028   0.00387  -0.0065   0.8139   0.0663
  -5.750  -0.6021   0.01009   0.00370  -0.0063   0.8126   0.0704
  -5.500  -0.5759   0.00990   0.00352  -0.0060   0.8112   0.0754
  -5.250  -0.5497   0.00971   0.00336  -0.0058   0.8098   0.0808
  -5.000  -0.5230   0.00955   0.00321  -0.0056   0.8083   0.0856
  -4.750  -0.4968   0.00935   0.00305  -0.0054   0.8069   0.0932
  -4.500  -0.4700   0.00920   0.00291  -0.0052   0.8056   0.0991
  -4.250  -0.4436   0.00902   0.00277  -0.0050   0.8044   0.1081
  -4.000  -0.4168   0.00886   0.00264  -0.0049   0.8032   0.1167
  -3.750  -0.3899   0.00872   0.00253  -0.0047   0.8021   0.1252
  -3.500  -0.3632   0.00856   0.00242  -0.0046   0.8008   0.1369
  -3.250  -0.3363   0.00839   0.00231  -0.0045   0.7996   0.1507
  -3.000  -0.3093   0.00822   0.00221  -0.0044   0.7984   0.1650
  -2.750  -0.2824   0.00804   0.00211  -0.0042   0.7972   0.1840
  -2.500  -0.2556   0.00785   0.00202  -0.0041   0.7959   0.2054
  -2.250  -0.2290   0.00765   0.00193  -0.0039   0.7943   0.2316
  -2.000  -0.2026   0.00741   0.00184  -0.0037   0.7926   0.2659
  -1.750  -0.1764   0.00718   0.00174  -0.0035   0.7903   0.3018
  -1.500  -0.1512   0.00690   0.00161  -0.0030   0.7840   0.3501
  -1.250  -0.1264   0.00652   0.00144  -0.0025   0.7724   0.4100
  -1.000  -0.1021   0.00612   0.00128  -0.0019   0.7604   0.4816
  -0.750  -0.0780   0.00572   0.00113  -0.0012   0.7527   0.5580
  -0.500  -0.0538   0.00531   0.00104  -0.0006   0.7451   0.6405
  -0.250  -0.0282   0.00512   0.00106  -0.0001   0.7362   0.7047
   0.000   0.0000   0.00510   0.00107   0.0000   0.7249   0.7246
   0.250   0.0281   0.00512   0.00106   0.0001   0.7045   0.7364
   0.500   0.0539   0.00530   0.00104   0.0006   0.6417   0.7451
   0.750   0.0780   0.00572   0.00113   0.0012   0.5584   0.7528
   1.000   0.1021   0.00612   0.00128   0.0019   0.4818   0.7605
   1.250   0.1263   0.00653   0.00144   0.0025   0.4090   0.7724
   1.500   0.1511   0.00690   0.00161   0.0031   0.3497   0.7840
   1.750   0.1764   0.00718   0.00174   0.0035   0.3019   0.7903
   2.000   0.2027   0.00741   0.00184   0.0037   0.2665   0.7926
   2.250   0.2289   0.00765   0.00193   0.0040   0.2315   0.7943
   2.500   0.2556   0.00785   0.00202   0.0041   0.2055   0.7959
   2.750   0.2824   0.00804   0.00212   0.0042   0.1833   0.7972
   3.000   0.3093   0.00822   0.00221   0.0044   0.1647   0.7984
   3.250   0.3363   0.00839   0.00231   0.0045   0.1505   0.7996
   3.500   0.3631   0.00856   0.00242   0.0046   0.1366   0.8008
   3.750   0.3898   0.00872   0.00253   0.0047   0.1252   0.8021
   4.000   0.4168   0.00886   0.00264   0.0049   0.1167   0.8032
   4.250   0.4436   0.00902   0.00277   0.0050   0.1081   0.8044
   4.500   0.4700   0.00920   0.00291   0.0052   0.0991   0.8056
   4.750   0.4968   0.00935   0.00305   0.0054   0.0933   0.8069
   5.000   0.5230   0.00955   0.00321   0.0056   0.0855   0.8083
   5.250   0.5497   0.00971   0.00336   0.0058   0.0808   0.8098
   5.500   0.5759   0.00990   0.00352   0.0060   0.0753   0.8112
   5.750   0.6021   0.01009   0.00370   0.0063   0.0705   0.8126
   6.000   0.6283   0.01028   0.00387   0.0065   0.0663   0.8139
   6.250   0.6539   0.01052   0.00407   0.0068   0.0613   0.8151
   6.500   0.6801   0.01070   0.00427   0.0070   0.0586   0.8163
   6.750   0.7054   0.01092   0.00447   0.0074   0.0545   0.8177
   7.000   0.7306   0.01115   0.00470   0.0078   0.0507   0.8193
   7.250   0.7559   0.01136   0.00492   0.0082   0.0480   0.8208
   7.500   0.7807   0.01161   0.00516   0.0086   0.0451   0.8224
   7.750   0.8054   0.01186   0.00542   0.0090   0.0425   0.8242
   8.000   0.8303   0.01209   0.00567   0.0095   0.0406   0.8262
   8.250   0.8546   0.01237   0.00594   0.0100   0.0379   0.8283
   8.500   0.8785   0.01267   0.00625   0.0105   0.0354   0.8302
   8.750   0.9028   0.01293   0.00652   0.0110   0.0340   0.8319
   9.000   0.9263   0.01321   0.00682   0.0116   0.0320   0.8339
   9.250   0.9491   0.01354   0.00716   0.0123   0.0298   0.8361
   9.500   0.9721   0.01384   0.00750   0.0130   0.0285   0.8385
   9.750   0.9948   0.01415   0.00784   0.0137   0.0270   0.8411
  10.000   1.0167   0.01451   0.00820   0.0146   0.0253   0.8438
  10.250   1.0383   0.01489   0.00860   0.0154   0.0238   0.8466
  10.500   1.0598   0.01522   0.00898   0.0163   0.0227   0.8494
  10.750   1.0803   0.01559   0.00939   0.0174   0.0215   0.8528
  11.000   1.0995   0.01600   0.00982   0.0186   0.0204   0.8568
  11.250   1.1169   0.01641   0.01028   0.0202   0.0195   0.8614
  11.500   1.1342   0.01678   0.01071   0.0218   0.0189   0.8663
  11.750   1.1507   0.01719   0.01119   0.0235   0.0182   0.8725
  12.000   1.1668   0.01764   0.01170   0.0251   0.0174   0.8792
  12.250   1.1816   0.01814   0.01225   0.0270   0.0166   0.8876
  12.500   1.1954   0.01869   0.01288   0.0289   0.0159   0.8981
  12.750   1.2093   0.01915   0.01345   0.0308   0.0156   0.9138
  13.000   1.2243   0.01962   0.01406   0.0325   0.0153   0.9449
  13.500   1.2698   0.02100   0.01558   0.0319   0.0140   1.0000
  13.750   1.2832   0.02172   0.01635   0.0334   0.0138   1.0000
  14.000   1.2957   0.02252   0.01718   0.0348   0.0133   1.0000
  14.250   1.3068   0.02342   0.01813   0.0364   0.0129   1.0000
  14.500   1.3179   0.02431   0.01909   0.0378   0.0126   1.0000
  14.750   1.3291   0.02522   0.02008   0.0392   0.0124   1.0000
  15.000   1.3395   0.02620   0.02112   0.0406   0.0121   1.0000
  15.250   1.3489   0.02726   0.02226   0.0419   0.0119   1.0000
  15.500   1.3582   0.02835   0.02341   0.0431   0.0116   1.0000
  15.750   1.3652   0.02963   0.02477   0.0444   0.0115   1.0000
  16.000   1.3716   0.03101   0.02622   0.0456   0.0112   1.0000
  16.250   1.3770   0.03250   0.02777   0.0467   0.0109   1.0000
  16.500   1.3807   0.03418   0.02953   0.0477   0.0107   1.0000
  16.750   1.3828   0.03606   0.03150   0.0485   0.0105   1.0000
  17.000   1.3820   0.03829   0.03381   0.0492   0.0102   1.0000
  17.250   1.3794   0.04081   0.03644   0.0496   0.0101   1.0000
  17.500   1.3744   0.04376   0.03949   0.0496   0.0099   1.0000
  17.750   1.3701   0.04686   0.04270   0.0492   0.0099   1.0000
  18.000   1.3632   0.05057   0.04654   0.0482   0.0098   1.0000
  18.250   1.3529   0.05506   0.05116   0.0464   0.0098   1.0000
  18.500   1.3385   0.06059   0.05684   0.0436   0.0097   1.0000
  18.750   1.3147   0.06819   0.06462   0.0392   0.0097   1.0000
  19.000   1.2777   0.07874   0.07538   0.0328   0.0097   1.0000
  19.250   1.2087   0.09577   0.09270   0.0225   0.0099   1.0000
<< Back to S1012 (s1012-il)

Polar data table (+)

Polar graphs


<< Back to S1012 (s1012-il)