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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 50,000
Max Cl/Cd: 42.51 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx601001-il-50000-n5.txt
Download as CSV file: xf-fx601001-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 (126) AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3768   0.10042   0.09346  -0.0381   1.0000   0.0458
  -9.000  -0.3770   0.09670   0.08983  -0.0391   1.0000   0.0450
  -8.750  -0.3790   0.09288   0.08611  -0.0402   1.0000   0.0443
  -8.500  -0.3829   0.08904   0.08238  -0.0413   1.0000   0.0435
  -8.250  -0.3893   0.08514   0.07860  -0.0422   1.0000   0.0428
  -8.000  -0.3996   0.08112   0.07473  -0.0431   1.0000   0.0421
  -7.500  -0.4356   0.06710   0.06084  -0.0551   1.0000   0.0392
  -7.250  -0.4393   0.06270   0.05640  -0.0580   1.0000   0.0390
  -7.000  -0.4401   0.05805   0.05161  -0.0610   1.0000   0.0388
  -6.750  -0.4359   0.05325   0.04655  -0.0643   1.0000   0.0388
  -6.500  -0.4253   0.04849   0.04140  -0.0676   1.0000   0.0389
  -6.250  -0.4083   0.04379   0.03614  -0.0707   1.0000   0.0392
  -6.000  -0.3899   0.04050   0.03262  -0.0722   1.0000   0.0406
  -5.750  -0.3698   0.03818   0.03002  -0.0731   1.0000   0.0435
  -5.500  -0.3450   0.03529   0.02659  -0.0745   1.0000   0.0472
  -5.250  -0.3184   0.03260   0.02325  -0.0753   1.0000   0.0497
  -5.000  -0.2958   0.03041   0.02099  -0.0753   1.0000   0.0530
  -4.750  -0.2719   0.02884   0.01916  -0.0751   1.0000   0.0602
  -4.500  -0.2483   0.02737   0.01759  -0.0750   1.0000   0.0700
  -4.250  -0.2236   0.02588   0.01600  -0.0749   1.0000   0.0835
  -4.000  -0.1975   0.02467   0.01481  -0.0758   1.0000   0.1116
  -3.750  -0.1686   0.02354   0.01366  -0.0771   0.9993   0.1432
  -3.500  -0.1254   0.02222   0.01257  -0.0814   0.9936   0.2026
  -3.250  -0.0861   0.02143   0.01270  -0.0843   0.9872   0.3549
  -3.000  -0.0497   0.02205   0.01315  -0.0857   0.9781   0.4520
  -2.750  -0.0144   0.02258   0.01340  -0.0870   0.9688   0.5079
  -2.500   0.0139   0.02310   0.01394  -0.0863   0.9591   0.5558
  -2.250   0.0455   0.02336   0.01410  -0.0865   0.9506   0.5888
  -2.000   0.0792   0.02339   0.01390  -0.0877   0.9414   0.6086
  -1.750   0.1124   0.02339   0.01372  -0.0888   0.9320   0.6238
  -1.500   0.1506   0.02338   0.01352  -0.0909   0.9247   0.6380
  -1.250   0.1819   0.02338   0.01335  -0.0918   0.9143   0.6507
  -1.000   0.2147   0.02338   0.01325  -0.0928   0.9050   0.6639
  -0.750   0.2513   0.02335   0.01311  -0.0945   0.8972   0.6781
  -0.500   0.2821   0.02336   0.01305  -0.0952   0.8869   0.6900
  -0.250   0.3176   0.02333   0.01294  -0.0968   0.8783   0.7000
   0.000   0.3537   0.02330   0.01282  -0.0985   0.8697   0.7095
   0.250   0.3841   0.02330   0.01280  -0.0992   0.8593   0.7176
   0.500   0.4182   0.02329   0.01275  -0.1004   0.8502   0.7265
   0.750   0.4529   0.02322   0.01268  -0.1017   0.8414   0.7356
   1.000   0.4827   0.02325   0.01273  -0.1021   0.8303   0.7446
   1.250   0.5144   0.02323   0.01275  -0.1028   0.8197   0.7548
   1.500   0.5486   0.02308   0.01264  -0.1037   0.8099   0.7659
   1.750   0.5798   0.02294   0.01257  -0.1039   0.7983   0.7781
   2.000   0.6083   0.02285   0.01260  -0.1037   0.7853   0.7923
   2.250   0.6360   0.02274   0.01262  -0.1034   0.7725   0.8100
   2.500   0.6622   0.02258   0.01264  -0.1026   0.7599   0.8353
   2.750   0.6886   0.02230   0.01262  -0.1017   0.7468   1.0000
   3.000   0.7227   0.02241   0.01273  -0.1029   0.7337   1.0000
   3.250   0.7553   0.02251   0.01285  -0.1036   0.7197   1.0000
   3.500   0.7864   0.02261   0.01302  -0.1039   0.7044   1.0000
   3.750   0.8164   0.02267   0.01311  -0.1039   0.6875   1.0000
   4.000   0.8464   0.02268   0.01315  -0.1036   0.6696   1.0000
   4.250   0.8756   0.02270   0.01319  -0.1032   0.6507   1.0000
   4.500   0.9019   0.02289   0.01350  -0.1025   0.6299   1.0000
   4.750   0.9300   0.02302   0.01368  -0.1019   0.6101   1.0000
   5.000   0.9555   0.02330   0.01405  -0.1011   0.5883   1.0000
   5.250   0.9819   0.02354   0.01437  -0.1003   0.5662   1.0000
   5.500   1.0060   0.02393   0.01493  -0.0993   0.5417   1.0000
   5.750   1.0302   0.02432   0.01541  -0.0982   0.5160   1.0000
   6.000   1.0534   0.02478   0.01596  -0.0971   0.4888   1.0000
   6.250   1.0755   0.02531   0.01659  -0.0959   0.4596   1.0000
   6.500   1.0971   0.02589   0.01725  -0.0946   0.4299   1.0000
   6.750   1.1177   0.02656   0.01792  -0.0931   0.3994   1.0000
   7.000   1.1371   0.02736   0.01880  -0.0916   0.3692   1.0000
   7.250   1.1560   0.02831   0.01974  -0.0902   0.3411   1.0000
   7.500   1.1741   0.02936   0.02083  -0.0887   0.3146   1.0000
   7.750   1.1880   0.03051   0.02200  -0.0868   0.2837   1.0000
   8.000   1.1947   0.03178   0.02315  -0.0843   0.2442   1.0000
   8.250   1.1974   0.03331   0.02449  -0.0818   0.1968   1.0000
   8.500   1.2006   0.03516   0.02615  -0.0794   0.1513   1.0000
   8.750   1.2011   0.03739   0.02814  -0.0769   0.1030   1.0000
   9.000   1.1978   0.04026   0.03070  -0.0742   0.0755   1.0000
   9.250   1.1960   0.04318   0.03355  -0.0719   0.0622   1.0000
   9.500   1.1937   0.04618   0.03649  -0.0699   0.0547   1.0000
   9.750   1.1959   0.04889   0.03939  -0.0683   0.0482   1.0000
  10.000   1.1945   0.05195   0.04250  -0.0670   0.0445   1.0000
  10.250   1.1982   0.05481   0.04558  -0.0657   0.0415   1.0000
  10.500   1.2026   0.05771   0.04869  -0.0645   0.0392   1.0000
  10.750   1.2062   0.06073   0.05184  -0.0636   0.0372   1.0000
  11.000   1.2102   0.06387   0.05506  -0.0628   0.0353   1.0000
  11.250   1.2159   0.06711   0.05866  -0.0620   0.0334   1.0000
  11.500   1.2180   0.07068   0.06252  -0.0616   0.0317   1.0000
  11.750   1.2181   0.07452   0.06659  -0.0615   0.0306   1.0000
  12.000   1.2168   0.07865   0.07110  -0.0617   0.0298   1.0000
  12.250   1.2135   0.08315   0.07584  -0.0623   0.0293   1.0000
  12.500   1.2077   0.08809   0.08101  -0.0633   0.0290   1.0000
  12.750   1.1993   0.09352   0.08669  -0.0649   0.0287   1.0000
  13.000   1.1881   0.09957   0.09299  -0.0674   0.0286   1.0000
  13.250   1.1737   0.10644   0.10011  -0.0708   0.0287   1.0000
  13.500   1.1560   0.11441   0.10835  -0.0754   0.0289   1.0000
  13.750   1.1350   0.12397   0.11818  -0.0816   0.0293   1.0000
  14.000   1.1102   0.13584   0.13016  -0.0895   0.0301   1.0000
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