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

SIKORSKY GS-1 AIRFOIL (gs1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SIKORSKY GS-1 AIRFOIL (gs1-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.78 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-gs1-il-1000000-n5.txt
Download as CSV file: xf-gs1-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SIKORSKY GS-1 AIRFOIL                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.8683   0.08466   0.08170  -0.0677   1.0000   0.0249
 -16.750  -0.8880   0.07835   0.07531  -0.0715   1.0000   0.0251
 -16.500  -0.9117   0.07170   0.06858  -0.0755   1.0000   0.0252
 -16.250  -0.9428   0.06440   0.06120  -0.0800   1.0000   0.0252
 -16.000  -0.9812   0.05640   0.05308  -0.0850   1.0000   0.0253
 -15.750  -1.0195   0.04858   0.04513  -0.0899   1.0000   0.0252
 -15.500  -1.0646   0.03987   0.03628  -0.0954   1.0000   0.0252
 -15.250  -1.1026   0.03056   0.02674  -0.1040   1.0000   0.0251
 -15.000  -1.1211   0.02716   0.02317  -0.1048   0.9982   0.0252
 -14.750  -1.1019   0.02510   0.02101  -0.1074   0.9936   0.0255
 -14.500  -1.0824   0.02372   0.01955  -0.1085   0.9894   0.0258
 -14.250  -1.0588   0.02257   0.01832  -0.1098   0.9859   0.0260
 -14.000  -1.0318   0.02153   0.01722  -0.1113   0.9831   0.0263
 -13.750  -1.0050   0.02062   0.01624  -0.1125   0.9791   0.0265
 -13.500  -0.9767   0.01981   0.01536  -0.1137   0.9743   0.0268
 -13.250  -0.9455   0.01903   0.01452  -0.1154   0.9711   0.0272
 -13.000  -0.9158   0.01835   0.01377  -0.1167   0.9676   0.0275
 -12.750  -0.8890   0.01774   0.01309  -0.1172   0.9620   0.0278
 -12.500  -0.8598   0.01713   0.01241  -0.1182   0.9573   0.0281
 -12.250  -0.8328   0.01659   0.01180  -0.1186   0.9514   0.0283
 -12.000  -0.8070   0.01608   0.01122  -0.1187   0.9441   0.0286
 -11.750  -0.7807   0.01563   0.01069  -0.1187   0.9374   0.0288
 -11.500  -0.7572   0.01512   0.01011  -0.1183   0.9287   0.0291
 -11.250  -0.7331   0.01461   0.00954  -0.1179   0.9204   0.0295
 -11.000  -0.7092   0.01417   0.00904  -0.1174   0.9110   0.0299
 -10.750  -0.6846   0.01378   0.00859  -0.1170   0.9023   0.0303
 -10.500  -0.6600   0.01343   0.00817  -0.1165   0.8920   0.0307
 -10.250  -0.6351   0.01310   0.00778  -0.1160   0.8823   0.0312
 -10.000  -0.6101   0.01280   0.00740  -0.1155   0.8723   0.0316
  -9.750  -0.5848   0.01252   0.00706  -0.1151   0.8621   0.0321
  -9.500  -0.5593   0.01227   0.00673  -0.1146   0.8522   0.0327
  -9.250  -0.5336   0.01203   0.00641  -0.1142   0.8420   0.0331
  -9.000  -0.5083   0.01173   0.00605  -0.1137   0.8326   0.0337
  -8.750  -0.4827   0.01146   0.00573  -0.1133   0.8222   0.0344
  -8.500  -0.4567   0.01122   0.00544  -0.1129   0.8131   0.0353
  -8.250  -0.4307   0.01101   0.00517  -0.1125   0.8026   0.0361
  -8.000  -0.4043   0.01081   0.00491  -0.1121   0.7930   0.0369
  -7.750  -0.3780   0.01064   0.00467  -0.1117   0.7828   0.0377
  -7.500  -0.3514   0.01042   0.00442  -0.1114   0.7723   0.0389
  -7.250  -0.3251   0.01024   0.00418  -0.1110   0.7617   0.0403
  -7.000  -0.2985   0.01008   0.00397  -0.1106   0.7497   0.0418
  -6.750  -0.2716   0.00994   0.00378  -0.1103   0.7384   0.0432
  -6.500  -0.2452   0.00977   0.00357  -0.1100   0.7265   0.0454
  -6.250  -0.2185   0.00964   0.00339  -0.1096   0.7139   0.0478
  -6.000  -0.1915   0.00952   0.00322  -0.1093   0.7016   0.0499
  -5.750  -0.1648   0.00938   0.00305  -0.1090   0.6894   0.0527
  -5.500  -0.1380   0.00929   0.00289  -0.1086   0.6774   0.0554
  -5.250  -0.1109   0.00917   0.00275  -0.1084   0.6659   0.0587
  -5.000  -0.0838   0.00907   0.00262  -0.1081   0.6557   0.0622
  -4.750  -0.0567   0.00897   0.00249  -0.1078   0.6454   0.0662
  -4.500  -0.0294   0.00888   0.00237  -0.1075   0.6363   0.0710
  -4.250  -0.0022   0.00878   0.00226  -0.1073   0.6271   0.0769
  -3.750   0.0527   0.00860   0.00207  -0.1069   0.6109   0.0892
  -3.500   0.0803   0.00854   0.00200  -0.1066   0.6036   0.0952
  -3.250   0.1080   0.00846   0.00192  -0.1065   0.5960   0.1027
  -3.000   0.1353   0.00841   0.00186  -0.1062   0.5886   0.1102
  -2.750   0.1632   0.00834   0.00181  -0.1061   0.5815   0.1189
  -2.500   0.1907   0.00828   0.00176  -0.1058   0.5741   0.1278
  -2.250   0.2185   0.00826   0.00172  -0.1057   0.5674   0.1343
  -2.000   0.2462   0.00821   0.00168  -0.1055   0.5599   0.1419
  -1.750   0.2737   0.00820   0.00165  -0.1053   0.5530   0.1485
  -1.500   0.3016   0.00815   0.00161  -0.1051   0.5464   0.1564
  -1.250   0.3290   0.00814   0.00159  -0.1049   0.5386   0.1640
  -1.000   0.3567   0.00810   0.00157  -0.1047   0.5319   0.1749
  -0.750   0.3842   0.00807   0.00156  -0.1045   0.5243   0.1881
  -0.500   0.4114   0.00805   0.00156  -0.1042   0.5172   0.2040
  -0.250   0.4389   0.00801   0.00157  -0.1040   0.5097   0.2217
   0.000   0.4659   0.00802   0.00159  -0.1037   0.5020   0.2386
   0.250   0.4936   0.00800   0.00161  -0.1036   0.4951   0.2550
   0.500   0.5207   0.00803   0.00164  -0.1033   0.4869   0.2698
   0.750   0.5481   0.00804   0.00167  -0.1030   0.4801   0.2843
   1.000   0.5752   0.00807   0.00171  -0.1028   0.4719   0.2983
   1.250   0.6023   0.00811   0.00176  -0.1025   0.4647   0.3091
   1.500   0.6295   0.00815   0.00181  -0.1022   0.4567   0.3218
   1.750   0.6562   0.00821   0.00187  -0.1019   0.4491   0.3361
   2.000   0.6834   0.00824   0.00193  -0.1016   0.4419   0.3483
   2.250   0.7099   0.00832   0.00200  -0.1013   0.4345   0.3608
   2.500   0.7370   0.00835   0.00207  -0.1010   0.4284   0.3773
   2.750   0.7636   0.00841   0.00215  -0.1006   0.4209   0.3947
   3.000   0.7900   0.00847   0.00223  -0.1003   0.4144   0.4112
   3.250   0.8168   0.00851   0.00232  -0.0999   0.4085   0.4328
   3.500   0.8426   0.00854   0.00243  -0.0995   0.4019   0.4698
   3.750   0.8685   0.00853   0.00255  -0.0991   0.3959   0.5195
   4.000   0.8939   0.00852   0.00267  -0.0985   0.3886   0.5788
   4.250   0.9176   0.00844   0.00282  -0.0977   0.3813   0.6739
   4.500   0.9336   0.00800   0.00301  -0.0949   0.3732   0.9201
   4.750   0.9810   0.00819   0.00318  -0.0992   0.3594   1.0000
   5.000   1.0050   0.00840   0.00333  -0.0984   0.3470   1.0000
   5.250   1.0288   0.00863   0.00348  -0.0976   0.3342   1.0000
   5.500   1.0530   0.00882   0.00363  -0.0968   0.3228   1.0000
   5.750   1.0766   0.00905   0.00380  -0.0960   0.3112   1.0000
   6.000   1.0994   0.00931   0.00400  -0.0950   0.2974   1.0000
   6.250   1.1220   0.00958   0.00420  -0.0940   0.2846   1.0000
   6.500   1.1442   0.00987   0.00442  -0.0929   0.2703   1.0000
   6.750   1.1648   0.01023   0.00468  -0.0916   0.2525   1.0000
   7.000   1.1848   0.01060   0.00496  -0.0902   0.2344   1.0000
   7.250   1.2036   0.01102   0.00527  -0.0886   0.2146   1.0000
   7.500   1.2216   0.01145   0.00560  -0.0869   0.1960   1.0000
   7.750   1.2365   0.01194   0.00598  -0.0846   0.1757   1.0000
   8.000   1.2462   0.01258   0.00646  -0.0814   0.1477   1.0000
   8.250   1.2529   0.01334   0.00705  -0.0777   0.1176   1.0000
   8.500   1.2607   0.01409   0.00766  -0.0744   0.0942   1.0000
   8.750   1.2730   0.01467   0.00817  -0.0719   0.0817   1.0000
   9.000   1.2864   0.01521   0.00867  -0.0696   0.0736   1.0000
   9.250   1.3016   0.01569   0.00913  -0.0677   0.0681   1.0000
   9.500   1.3157   0.01622   0.00965  -0.0656   0.0634   1.0000
   9.750   1.3310   0.01672   0.01015  -0.0638   0.0600   1.0000
  10.000   1.3444   0.01732   0.01074  -0.0618   0.0563   1.0000
  10.250   1.3594   0.01785   0.01129  -0.0601   0.0541   1.0000
  10.500   1.3737   0.01845   0.01189  -0.0584   0.0517   1.0000
  10.750   1.3862   0.01916   0.01260  -0.0565   0.0493   1.0000
  11.000   1.3998   0.01983   0.01329  -0.0549   0.0472   1.0000
  11.250   1.4132   0.02054   0.01402  -0.0532   0.0455   1.0000
  11.500   1.4251   0.02136   0.01486  -0.0516   0.0437   1.0000
  11.750   1.4364   0.02226   0.01577  -0.0499   0.0420   1.0000
  12.000   1.4491   0.02310   0.01665  -0.0485   0.0410   1.0000
  12.250   1.4609   0.02403   0.01761  -0.0470   0.0397   1.0000
  12.500   1.4714   0.02508   0.01869  -0.0456   0.0384   1.0000
  12.750   1.4802   0.02629   0.01991  -0.0441   0.0370   1.0000
  13.000   1.4904   0.02744   0.02111  -0.0429   0.0361   1.0000
  13.250   1.5005   0.02865   0.02236  -0.0417   0.0352   1.0000
  13.500   1.5095   0.02997   0.02372  -0.0406   0.0341   1.0000
  13.750   1.5173   0.03144   0.02522  -0.0395   0.0332   1.0000
  14.000   1.5240   0.03305   0.02687  -0.0384   0.0323   1.0000
  14.250   1.5301   0.03477   0.02864  -0.0375   0.0315   1.0000
  14.500   1.5374   0.03643   0.03036  -0.0367   0.0309   1.0000
  14.750   1.5439   0.03822   0.03220  -0.0360   0.0302   1.0000
  15.000   1.5494   0.04016   0.03419  -0.0353   0.0294   1.0000
  15.250   1.5539   0.04225   0.03633  -0.0347   0.0287   1.0000
  15.500   1.5573   0.04450   0.03863  -0.0343   0.0280   1.0000
  15.750   1.5592   0.04695   0.04113  -0.0339   0.0272   1.0000
  16.000   1.5626   0.04931   0.04356  -0.0336   0.0267   1.0000
  16.250   1.5654   0.05179   0.04610  -0.0334   0.0262   1.0000
  16.500   1.5674   0.05438   0.04876  -0.0333   0.0255   1.0000
  16.750   1.5682   0.05716   0.05159  -0.0332   0.0248   1.0000
  17.000   1.5684   0.06007   0.05456  -0.0333   0.0243   1.0000
  17.250   1.5670   0.06323   0.05779  -0.0335   0.0237   1.0000
  17.500   1.5656   0.06645   0.06108  -0.0338   0.0232   1.0000
  17.750   1.5653   0.06958   0.06428  -0.0342   0.0228   1.0000
  18.000   1.5645   0.07282   0.06759  -0.0346   0.0223   1.0000
  18.250   1.5630   0.07622   0.07106  -0.0352   0.0216   1.0000
  18.500   1.5601   0.07987   0.07478  -0.0359   0.0212   1.0000
  18.750   1.5567   0.08362   0.07859  -0.0368   0.0206   1.0000
  19.000   1.5529   0.08750   0.08253  -0.0378   0.0200   1.0000
<< Back to SIKORSKY GS-1 AIRFOIL (gs1-il)

Polar data table (+)

Polar graphs


<< Back to SIKORSKY GS-1 AIRFOIL (gs1-il)