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FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 63-100 AIRFOIL (fx63100-il)
Reynolds number: 100,000
Max Cl/Cd: 67.73 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63100-il-100000-n5.txt
Download as CSV file: xf-fx63100-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-100 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3390   0.09292   0.08802  -0.0400   1.0000   0.0319
  -8.250  -0.3458   0.09009   0.08528  -0.0397   1.0000   0.0323
  -8.000  -0.3545   0.08762   0.08291  -0.0385   1.0000   0.0321
  -7.750  -0.3678   0.08556   0.08096  -0.0366   1.0000   0.0322
  -7.500  -0.3849   0.08393   0.07945  -0.0339   1.0000   0.0321
  -7.250  -0.3738   0.07850   0.07405  -0.0405   0.9936   0.0321
  -7.000  -0.3535   0.07090   0.06644  -0.0518   0.9845   0.0321
  -6.750  -0.3287   0.06072   0.05618  -0.0682   0.9745   0.0315
  -6.500  -0.2966   0.04867   0.04370  -0.0871   0.9655   0.0314
  -6.250  -0.2601   0.03967   0.03398  -0.0997   0.9580   0.0323
  -6.000  -0.2134   0.03302   0.02631  -0.1095   0.9549   0.0353
  -5.750  -0.1807   0.03015   0.02314  -0.1129   0.9487   0.0373
  -5.500  -0.1424   0.02789   0.02049  -0.1165   0.9446   0.0401
  -5.250  -0.1011   0.02584   0.01794  -0.1201   0.9417   0.0451
  -5.000  -0.0670   0.02391   0.01554  -0.1219   0.9356   0.0481
  -4.750  -0.0312   0.02273   0.01432  -0.1242   0.9312   0.0532
  -4.500   0.0076   0.02148   0.01281  -0.1264   0.9281   0.0579
  -4.250   0.0402   0.02055   0.01171  -0.1275   0.9220   0.0631
  -4.000   0.0755   0.01967   0.01083  -0.1292   0.9173   0.0676
  -3.750   0.1140   0.01893   0.00995  -0.1312   0.9138   0.0741
  -3.500   0.1485   0.01827   0.00934  -0.1328   0.9082   0.0820
  -3.250   0.1841   0.01765   0.00865  -0.1344   0.9026   0.0909
  -3.000   0.2237   0.01700   0.00797  -0.1369   0.8986   0.1065
  -2.750   0.2594   0.01639   0.00745  -0.1388   0.8925   0.1362
  -2.500   0.2975   0.01539   0.00707  -0.1417   0.8867   0.2682
  -2.250   0.3365   0.01487   0.00695  -0.1440   0.8821   0.4233
  -2.000   0.3661   0.01475   0.00705  -0.1440   0.8730   0.4946
  -1.750   0.4014   0.01465   0.00700  -0.1449   0.8665   0.5557
  -1.500   0.4302   0.01469   0.00702  -0.1447   0.8563   0.5950
  -1.000   0.4904   0.01465   0.00695  -0.1447   0.8394   0.6521
  -0.750   0.5198   0.01464   0.00692  -0.1445   0.8312   0.6763
  -0.500   0.5488   0.01463   0.00688  -0.1444   0.8225   0.6951
  -0.250   0.5769   0.01465   0.00687  -0.1441   0.8135   0.7113
   0.000   0.6068   0.01463   0.00680  -0.1442   0.8055   0.7276
   0.250   0.6332   0.01467   0.00685  -0.1436   0.7956   0.7435
   0.500   0.6623   0.01466   0.00680  -0.1435   0.7875   0.7596
   0.750   0.6883   0.01470   0.00686  -0.1429   0.7774   0.7758
   1.000   0.7148   0.01472   0.00690  -0.1423   0.7680   0.7927
   1.250   0.7418   0.01470   0.00688  -0.1417   0.7591   0.8105
   1.500   0.7651   0.01473   0.00697  -0.1405   0.7484   0.8295
   1.750   0.7891   0.01471   0.00701  -0.1394   0.7385   0.8525
   2.000   0.8118   0.01464   0.00698  -0.1379   0.7288   0.8838
   2.250   0.8345   0.01454   0.00696  -0.1365   0.7171   1.0000
   2.500   0.8654   0.01470   0.00711  -0.1371   0.7056   1.0000
   2.750   0.8955   0.01484   0.00721  -0.1375   0.6926   1.0000
   3.000   0.9242   0.01497   0.00730  -0.1375   0.6762   1.0000
   3.250   0.9523   0.01511   0.00742  -0.1374   0.6586   1.0000
   3.500   0.9802   0.01528   0.00756  -0.1372   0.6419   1.0000
   3.750   1.0078   0.01549   0.00776  -0.1370   0.6262   1.0000
   4.000   1.0350   0.01571   0.00800  -0.1368   0.6099   1.0000
   4.250   1.0619   0.01595   0.00824  -0.1365   0.5932   1.0000
   4.500   1.0881   0.01620   0.00848  -0.1360   0.5746   1.0000
   4.750   1.1131   0.01648   0.00879  -0.1353   0.5518   1.0000
   5.000   1.1372   0.01679   0.00904  -0.1344   0.5241   1.0000
   5.250   1.1603   0.01718   0.00933  -0.1334   0.4928   1.0000
   5.500   1.1828   0.01763   0.00969  -0.1323   0.4615   1.0000
   5.750   1.2046   0.01818   0.01014  -0.1312   0.4296   1.0000
   6.000   1.2246   0.01884   0.01064  -0.1299   0.3915   1.0000
   6.250   1.2431   0.01961   0.01123  -0.1284   0.3461   1.0000
   6.500   1.2604   0.02050   0.01190  -0.1268   0.2974   1.0000
   6.750   1.2770   0.02150   0.01270  -0.1252   0.2547   1.0000
   7.000   1.2936   0.02254   0.01358  -0.1237   0.2197   1.0000
   7.250   1.3099   0.02362   0.01454  -0.1221   0.1893   1.0000
   7.500   1.3257   0.02474   0.01556  -0.1206   0.1608   1.0000
   7.750   1.3405   0.02592   0.01666  -0.1189   0.1352   1.0000
   8.250   1.3658   0.02854   0.01914  -0.1150   0.1006   1.0000
   8.500   1.3763   0.02987   0.02048  -0.1127   0.0905   1.0000
   8.750   1.3858   0.03120   0.02187  -0.1103   0.0835   1.0000
   9.000   1.3938   0.03264   0.02337  -0.1078   0.0785   1.0000
   9.250   1.4000   0.03428   0.02504  -0.1052   0.0748   1.0000
   9.500   1.4097   0.03575   0.02667  -0.1031   0.0714   1.0000
   9.750   1.4187   0.03733   0.02841  -0.1011   0.0682   1.0000
  10.000   1.4265   0.03904   0.03019  -0.0992   0.0653   1.0000
  10.250   1.4338   0.04099   0.03216  -0.0973   0.0626   1.0000
  10.500   1.4453   0.04264   0.03402  -0.0958   0.0601   1.0000
  10.750   1.4557   0.04443   0.03599  -0.0943   0.0576   1.0000
  11.000   1.4644   0.04630   0.03798  -0.0929   0.0550   1.0000
  11.250   1.4710   0.04836   0.04009  -0.0916   0.0527   1.0000
  11.500   1.4791   0.05054   0.04244  -0.0903   0.0504   1.0000
  11.750   1.4861   0.05273   0.04489  -0.0891   0.0479   1.0000
  12.000   1.4907   0.05504   0.04742  -0.0880   0.0455   1.0000
  12.250   1.4938   0.05750   0.05000  -0.0870   0.0435   1.0000
  12.500   1.4968   0.06026   0.05277  -0.0862   0.0416   1.0000
  12.750   1.4977   0.06333   0.05619  -0.0854   0.0398   1.0000
  13.000   1.4974   0.06661   0.05975  -0.0849   0.0380   1.0000
  13.250   1.4956   0.07001   0.06334  -0.0846   0.0363   1.0000
  13.500   1.4930   0.07348   0.06694  -0.0846   0.0349   1.0000
  13.750   1.4908   0.07705   0.07059  -0.0847   0.0336   1.0000
  14.000   1.4850   0.08152   0.07527  -0.0851   0.0325   1.0000
  14.250   1.4750   0.08669   0.08079  -0.0860   0.0315   1.0000
  14.500   1.4630   0.09230   0.08672  -0.0876   0.0306   1.0000
  14.750   1.4502   0.09828   0.09298  -0.0897   0.0298   1.0000
  15.000   1.4368   0.10458   0.09954  -0.0924   0.0291   1.0000
  15.250   1.4226   0.11135   0.10655  -0.0957   0.0285   1.0000
  15.500   1.4072   0.11872   0.11415  -0.0998   0.0281   1.0000
  15.750   1.3916   0.12651   0.12215  -0.1045   0.0277   1.0000
  16.000   1.3679   0.13688   0.13279  -0.1112   0.0278   1.0000
  16.250   1.3239   0.15413   0.15039  -0.1234   0.0291   1.0000
  16.500   1.2491   0.18605   0.18243  -0.1455   0.0313   1.0000
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