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S4022 (s4022-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4022 (s4022-il)
Reynolds number: 100,000
Max Cl/Cd: 65.15 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4022-il-100000-n5.txt
Download as CSV file: xf-s4022-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4022                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3539   0.11193   0.10726  -0.0364   1.0000   0.0554
  -8.750  -0.3641   0.10979   0.10521  -0.0361   1.0000   0.0567
  -8.500  -0.3742   0.10695   0.10246  -0.0409   0.9974   0.0581
  -8.250  -0.3679   0.10237   0.09790  -0.0476   0.9920   0.0584
  -8.000  -0.3617   0.09770   0.09326  -0.0533   0.9859   0.0585
  -7.750  -0.3563   0.09276   0.08833  -0.0592   0.9785   0.0586
  -7.500  -0.3382   0.08424   0.07973  -0.0561   0.9778   0.0323
  -7.250  -0.3295   0.07963   0.07513  -0.0606   0.9720   0.0313
  -7.000  -0.3214   0.07426   0.06978  -0.0664   0.9635   0.0304
  -6.750  -0.3103   0.06629   0.06176  -0.0773   0.9542   0.0295
  -6.500  -0.2919   0.05743   0.05264  -0.0892   0.9477   0.0282
  -6.250  -0.2788   0.05069   0.04556  -0.0956   0.9386   0.0275
  -6.000  -0.2491   0.04502   0.03943  -0.1026   0.9347   0.0285
  -5.750  -0.2266   0.04100   0.03496  -0.1058   0.9276   0.0298
  -5.500  -0.1932   0.03675   0.03012  -0.1101   0.9238   0.0301
  -5.250  -0.1556   0.03302   0.02578  -0.1141   0.9214   0.0298
  -5.000  -0.1267   0.03051   0.02279  -0.1155   0.9161   0.0298
  -4.750  -0.0935   0.02831   0.02012  -0.1172   0.9120   0.0299
  -4.500  -0.0577   0.02646   0.01791  -0.1191   0.9093   0.0304
  -4.250  -0.0206   0.02491   0.01608  -0.1210   0.9071   0.0311
  -4.000   0.0042   0.02391   0.01493  -0.1206   0.9004   0.0320
  -3.750   0.0378   0.02298   0.01384  -0.1218   0.8967   0.0335
  -3.500   0.0743   0.02186   0.01273  -0.1240   0.8942   0.0386
  -3.250   0.1029   0.02123   0.01201  -0.1244   0.8884   0.0412
  -3.000   0.1365   0.02058   0.01120  -0.1256   0.8839   0.0444
  -2.750   0.1748   0.01980   0.01034  -0.1278   0.8812   0.0520
  -2.500   0.2160   0.01873   0.00953  -0.1309   0.8792   0.1176
  -2.250   0.2441   0.01755   0.00948  -0.1324   0.8723   0.3866
  -2.000   0.2755   0.01728   0.00985  -0.1326   0.8683   0.5890
  -1.750   0.3102   0.01721   0.00978  -0.1332   0.8655   0.6418
  -1.500   0.3322   0.01731   0.00980  -0.1319   0.8570   0.6655
  -1.000   0.3940   0.01717   0.00950  -0.1324   0.8467   0.7071
  -0.750   0.4247   0.01709   0.00934  -0.1327   0.8411   0.7237
  -0.500   0.4617   0.01689   0.00906  -0.1342   0.8376   0.7394
  -0.250   0.4847   0.01694   0.00908  -0.1331   0.8289   0.7528
   0.000   0.5202   0.01675   0.00882  -0.1344   0.8245   0.7662
   0.250   0.5451   0.01678   0.00881  -0.1337   0.8162   0.7790
   0.500   0.5792   0.01661   0.00860  -0.1347   0.8109   0.7921
   0.750   0.6046   0.01661   0.00860  -0.1341   0.8027   0.8054
   1.000   0.6374   0.01645   0.00842  -0.1348   0.7968   0.8190
   1.250   0.6614   0.01645   0.00844  -0.1339   0.7881   0.8334
   1.500   0.6936   0.01627   0.00826  -0.1345   0.7820   0.8485
   1.750   0.7149   0.01628   0.00832  -0.1330   0.7724   0.8662
   2.000   0.7443   0.01611   0.00817  -0.1330   0.7654   0.8874
   2.250   0.7672   0.01602   0.00814  -0.1319   0.7559   0.9187
   2.500   0.7982   0.01593   0.00810  -0.1326   0.7465   1.0000
   2.750   0.8367   0.01591   0.00803  -0.1347   0.7388   1.0000
   3.000   0.8650   0.01608   0.00820  -0.1351   0.7278   1.0000
   3.250   0.8949   0.01621   0.00834  -0.1357   0.7171   1.0000
   3.500   0.9263   0.01630   0.00845  -0.1364   0.7067   1.0000
   3.750   0.9583   0.01637   0.00851  -0.1372   0.6960   1.0000
   4.000   0.9860   0.01652   0.00869  -0.1372   0.6834   1.0000
   4.250   1.0133   0.01668   0.00887  -0.1371   0.6701   1.0000
   4.500   1.0404   0.01685   0.00910  -0.1369   0.6563   1.0000
   4.750   1.0673   0.01702   0.00929  -0.1367   0.6417   1.0000
   5.000   1.0941   0.01719   0.00948  -0.1364   0.6261   1.0000
   5.250   1.1181   0.01742   0.00974  -0.1356   0.6085   1.0000
   5.500   1.1419   0.01766   0.01001  -0.1348   0.5899   1.0000
   5.750   1.1660   0.01792   0.01032  -0.1340   0.5706   1.0000
   6.000   1.1876   0.01823   0.01066  -0.1327   0.5492   1.0000
   6.250   1.2091   0.01858   0.01098  -0.1314   0.5260   1.0000
   6.500   1.2281   0.01899   0.01139  -0.1298   0.5005   1.0000
   6.750   1.2460   0.01946   0.01183  -0.1280   0.4733   1.0000
   7.000   1.2624   0.02000   0.01232  -0.1259   0.4441   1.0000
   7.250   1.2770   0.02062   0.01293  -0.1236   0.4137   1.0000
   7.500   1.2890   0.02131   0.01355  -0.1208   0.3817   1.0000
   7.750   1.2992   0.02211   0.01426  -0.1179   0.3476   1.0000
   8.250   1.3156   0.02409   0.01601  -0.1119   0.2787   1.0000
   8.500   1.3222   0.02527   0.01706  -0.1088   0.2459   1.0000
   8.750   1.3280   0.02656   0.01824  -0.1059   0.2157   1.0000
   9.000   1.3337   0.02794   0.01952  -0.1030   0.1876   1.0000
   9.250   1.3397   0.02937   0.02094  -0.1004   0.1633   1.0000
   9.500   1.3455   0.03087   0.02242  -0.0979   0.1439   1.0000
   9.750   1.3511   0.03246   0.02400  -0.0954   0.1264   1.0000
  10.000   1.3555   0.03418   0.02569  -0.0931   0.1101   1.0000
  10.500   1.3640   0.03782   0.02926  -0.0890   0.0781   1.0000
  10.750   1.3686   0.03972   0.03115  -0.0872   0.0638   1.0000
  11.000   1.3722   0.04177   0.03324  -0.0854   0.0541   1.0000
  11.250   1.3735   0.04411   0.03559  -0.0837   0.0459   1.0000
  11.500   1.3760   0.04645   0.03810  -0.0820   0.0385   1.0000
  11.750   1.3738   0.04933   0.04109  -0.0804   0.0334   1.0000
  12.000   1.3729   0.05221   0.04414  -0.0789   0.0292   1.0000
  12.250   1.3688   0.05549   0.04750  -0.0778   0.0264   1.0000
  12.500   1.3665   0.05873   0.05090  -0.0768   0.0242   1.0000
  12.750   1.3660   0.06186   0.05423  -0.0760   0.0221   1.0000
  13.000   1.3647   0.06516   0.05768  -0.0756   0.0204   1.0000
  13.250   1.3613   0.06884   0.06149  -0.0754   0.0192   1.0000
  13.500   1.3554   0.07299   0.06578  -0.0754   0.0183   1.0000
  13.750   1.3520   0.07697   0.06993  -0.0754   0.0177   1.0000
  14.000   1.3504   0.08085   0.07403  -0.0755   0.0172   1.0000
  14.250   1.3485   0.08489   0.07830  -0.0758   0.0167   1.0000
  14.500   1.3459   0.08912   0.08275  -0.0764   0.0162   1.0000
  14.750   1.3424   0.09359   0.08745  -0.0772   0.0158   1.0000
  15.000   1.3380   0.09834   0.09243  -0.0783   0.0154   1.0000
  15.250   1.3323   0.10342   0.09774  -0.0798   0.0151   1.0000
  15.500   1.3252   0.10886   0.10341  -0.0818   0.0149   1.0000
  15.750   1.3167   0.11472   0.10950  -0.0843   0.0148   1.0000
  16.000   1.3069   0.12103   0.11604  -0.0874   0.0146   1.0000
  16.250   1.2957   0.12787   0.12311  -0.0911   0.0145   1.0000
  16.500   1.2830   0.13534   0.13080  -0.0955   0.0144   1.0000
  16.750   1.2683   0.14369   0.13938  -0.1008   0.0145   1.0000
  17.000   1.2513   0.15311   0.14902  -0.1070   0.0147   1.0000
  17.250   1.2311   0.16420   0.16031  -0.1146   0.0149   1.0000
  17.500   1.2060   0.17806   0.17433  -0.1241   0.0154   1.0000
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