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S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S8052 (11.88%) (s8052-il)
Reynolds number: 100,000
Max Cl/Cd: 46.33 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8052-il-100000-n5.txt
Download as CSV file: xf-s8052-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8052 (11.88%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5196   0.09441   0.08932  -0.0267   1.0000   0.0250
 -10.500  -0.5908   0.06993   0.06467  -0.0448   1.0000   0.0222
 -10.250  -0.6101   0.06418   0.05881  -0.0488   1.0000   0.0221
 -10.000  -0.6265   0.05982   0.05435  -0.0507   1.0000   0.0220
  -9.750  -0.6456   0.05602   0.05040  -0.0508   1.0000   0.0219
  -9.500  -0.6610   0.05276   0.04695  -0.0493   1.0000   0.0219
  -9.250  -0.6707   0.04936   0.04328  -0.0478   1.0000   0.0220
  -9.000  -0.6766   0.04607   0.03962  -0.0460   1.0000   0.0221
  -8.750  -0.6769   0.04319   0.03645  -0.0441   1.0000   0.0225
  -8.500  -0.6711   0.04101   0.03415  -0.0425   1.0000   0.0230
  -8.250  -0.6645   0.03935   0.03239  -0.0405   1.0000   0.0236
  -8.000  -0.6605   0.03770   0.03059  -0.0378   1.0000   0.0242
  -7.750  -0.6582   0.03612   0.02881  -0.0346   0.9996   0.0246
  -7.500  -0.6310   0.03339   0.02564  -0.0361   0.9891   0.0250
  -7.250  -0.6013   0.03087   0.02273  -0.0375   0.9810   0.0256
  -7.000  -0.5707   0.02875   0.02028  -0.0387   0.9735   0.0263
  -6.750  -0.5387   0.02691   0.01818  -0.0400   0.9671   0.0271
  -6.500  -0.5074   0.02535   0.01639  -0.0410   0.9598   0.0282
  -6.250  -0.4771   0.02390   0.01486  -0.0420   0.9531   0.0293
  -6.000  -0.4481   0.02283   0.01376  -0.0429   0.9453   0.0316
  -5.750  -0.4182   0.02191   0.01271  -0.0436   0.9385   0.0350
  -5.500  -0.3916   0.02091   0.01168  -0.0439   0.9305   0.0390
  -5.250  -0.3642   0.02005   0.01068  -0.0440   0.9232   0.0447
  -5.000  -0.3390   0.01919   0.00980  -0.0438   0.9154   0.0556
  -4.750  -0.3145   0.01824   0.00907  -0.0436   0.9082   0.0854
  -4.500  -0.2920   0.01733   0.00854  -0.0432   0.9005   0.1501
  -4.250  -0.2696   0.01645   0.00810  -0.0427   0.8938   0.2421
  -4.000  -0.2488   0.01571   0.00779  -0.0418   0.8863   0.3386
  -3.750  -0.2267   0.01505   0.00757  -0.0408   0.8804   0.4430
  -3.500  -0.2067   0.01472   0.00764  -0.0390   0.8729   0.5387
  -3.250  -0.1818   0.01465   0.00768  -0.0378   0.8675   0.6099
  -3.000  -0.1584   0.01470   0.00773  -0.0364   0.8606   0.6556
  -2.750  -0.1334   0.01475   0.00774  -0.0353   0.8546   0.6899
  -2.500  -0.1080   0.01481   0.00772  -0.0342   0.8489   0.7175
  -2.250  -0.0840   0.01488   0.00772  -0.0330   0.8419   0.7412
  -2.000  -0.0577   0.01492   0.00769  -0.0321   0.8368   0.7614
  -1.750  -0.0338   0.01500   0.00772  -0.0308   0.8295   0.7795
  -1.500  -0.0080   0.01503   0.00767  -0.0299   0.8236   0.7963
  -1.250   0.0174   0.01506   0.00765  -0.0289   0.8173   0.8116
  -1.000   0.0428   0.01510   0.00763  -0.0281   0.8105   0.8260
  -0.750   0.0702   0.01509   0.00754  -0.0274   0.8053   0.8395
  -0.500   0.0951   0.01513   0.00756  -0.0266   0.7972   0.8529
  -0.250   0.1228   0.01511   0.00747  -0.0261   0.7913   0.8658
   0.000   0.1502   0.01514   0.00749  -0.0258   0.7830   0.8776
   0.250   0.1809   0.01511   0.00740  -0.0259   0.7765   0.8884
   0.500   0.2095   0.01512   0.00741  -0.0258   0.7680   0.8996
   0.750   0.2396   0.01506   0.00730  -0.0259   0.7608   0.9107
   1.000   0.2727   0.01506   0.00729  -0.0268   0.7508   0.9193
   1.250   0.3052   0.01499   0.00719  -0.0275   0.7421   0.9285
   1.500   0.3387   0.01493   0.00710  -0.0284   0.7314   0.9371
   1.750   0.3728   0.01487   0.00705  -0.0296   0.7195   0.9454
   2.000   0.4062   0.01480   0.00697  -0.0306   0.7073   0.9547
   2.250   0.4428   0.01471   0.00688  -0.0322   0.6944   0.9621
   2.500   0.4774   0.01463   0.00680  -0.0335   0.6803   0.9711
   2.750   0.5137   0.01455   0.00674  -0.0352   0.6642   0.9798
   3.000   0.5494   0.01448   0.00668  -0.0369   0.6459   0.9893
   3.250   0.5851   0.01440   0.00661  -0.0386   0.6256   0.9996
   3.500   0.6025   0.01440   0.00661  -0.0367   0.6059   1.0000
   3.750   0.6200   0.01444   0.00660  -0.0348   0.5843   1.0000
   4.000   0.6386   0.01450   0.00659  -0.0330   0.5605   1.0000
   4.250   0.6577   0.01463   0.00662  -0.0313   0.5345   1.0000
   4.500   0.6771   0.01483   0.00670  -0.0297   0.5050   1.0000
   4.750   0.6967   0.01510   0.00684  -0.0282   0.4732   1.0000
   5.000   0.7163   0.01546   0.00705  -0.0267   0.4405   1.0000
   5.250   0.7357   0.01588   0.00734  -0.0253   0.4070   1.0000
   5.500   0.7549   0.01637   0.00767  -0.0239   0.3745   1.0000
   5.750   0.7741   0.01690   0.00805  -0.0226   0.3439   1.0000
   6.000   0.7933   0.01746   0.00848  -0.0213   0.3154   1.0000
   6.250   0.8125   0.01804   0.00897  -0.0201   0.2903   1.0000
   6.500   0.8317   0.01865   0.00947  -0.0190   0.2677   1.0000
   6.750   0.8511   0.01926   0.01001  -0.0179   0.2484   1.0000
   7.000   0.8707   0.01987   0.01058  -0.0168   0.2309   1.0000
   7.250   0.8901   0.02050   0.01120  -0.0157   0.2155   1.0000
   7.500   0.9092   0.02115   0.01183  -0.0146   0.2011   1.0000
   7.750   0.9279   0.02182   0.01248  -0.0135   0.1880   1.0000
   8.000   0.9460   0.02253   0.01317  -0.0124   0.1759   1.0000
   8.250   0.9637   0.02325   0.01391  -0.0112   0.1640   1.0000
   8.500   0.9818   0.02395   0.01467  -0.0100   0.1527   1.0000
   8.750   0.9988   0.02472   0.01546  -0.0088   0.1422   1.0000
   9.000   1.0143   0.02555   0.01629  -0.0075   0.1330   1.0000
   9.250   1.0299   0.02637   0.01717  -0.0061   0.1241   1.0000
   9.500   1.0446   0.02725   0.01813  -0.0047   0.1158   1.0000
   9.750   1.0559   0.02818   0.01906  -0.0029   0.1089   1.0000
  10.000   1.0694   0.02914   0.02013  -0.0013   0.1021   1.0000
  10.250   1.0801   0.03018   0.02120   0.0004   0.0966   1.0000
  10.500   1.0917   0.03131   0.02242   0.0019   0.0910   1.0000
  10.750   1.1024   0.03246   0.02366   0.0033   0.0860   1.0000
  11.000   1.1106   0.03381   0.02499   0.0048   0.0821   1.0000
  11.250   1.1227   0.03514   0.02652   0.0060   0.0783   1.0000
  11.500   1.1325   0.03656   0.02806   0.0072   0.0749   1.0000
  11.750   1.1405   0.03806   0.02961   0.0084   0.0721   1.0000
  12.000   1.1487   0.03975   0.03135   0.0095   0.0694   1.0000
  12.250   1.1569   0.04146   0.03330   0.0104   0.0665   1.0000
  12.500   1.1636   0.04326   0.03525   0.0113   0.0640   1.0000
  12.750   1.1695   0.04516   0.03726   0.0121   0.0620   1.0000
  13.000   1.1752   0.04715   0.03934   0.0128   0.0604   1.0000
  13.250   1.1818   0.04932   0.04155   0.0135   0.0588   1.0000
  13.500   1.1823   0.05195   0.04449   0.0140   0.0573   1.0000
  13.750   1.1810   0.05482   0.04761   0.0142   0.0558   1.0000
  14.000   1.1783   0.05788   0.05090   0.0142   0.0544   1.0000
  14.250   1.1741   0.06113   0.05434   0.0140   0.0530   1.0000
  14.500   1.1695   0.06454   0.05791   0.0134   0.0519   1.0000
  14.750   1.1642   0.06820   0.06174   0.0126   0.0510   1.0000
  15.000   1.1589   0.07197   0.06563   0.0116   0.0501   1.0000
  15.250   1.1550   0.07571   0.06947   0.0105   0.0492   1.0000
  15.500   1.1468   0.08027   0.07412   0.0089   0.0484   1.0000
  15.750   1.1255   0.08706   0.08119   0.0055   0.0482   1.0000
  16.000   1.1000   0.09513   0.08951   0.0009   0.0480   1.0000
  16.250   1.0689   0.10504   0.09966  -0.0052   0.0480   1.0000
  16.500   1.0262   0.11848   0.11331  -0.0139   0.0483   1.0000
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