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FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 63-110 AIRFOIL (fx63110-il)
Reynolds number: 100,000
Max Cl/Cd: 66.06 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63110-il-100000-n5.txt
Download as CSV file: xf-fx63110-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-110 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3438   0.09287   0.08787  -0.0442   1.0000   0.0376
  -8.750  -0.3504   0.08969   0.08478  -0.0440   1.0000   0.0375
  -8.500  -0.3606   0.08668   0.08187  -0.0433   1.0000   0.0374
  -8.250  -0.3742   0.08420   0.07950  -0.0418   1.0000   0.0371
  -8.000  -0.3931   0.08213   0.07755  -0.0394   0.9999   0.0370
  -7.750  -0.3839   0.07466   0.07010  -0.0492   0.9898   0.0378
  -7.500  -0.3698   0.06141   0.05676  -0.0690   0.9769   0.0383
  -7.250  -0.3504   0.04774   0.04246  -0.0911   0.9639   0.0390
  -7.000  -0.3209   0.03997   0.03388  -0.1018   0.9553   0.0400
  -6.750  -0.2892   0.03538   0.02885  -0.1077   0.9494   0.0421
  -6.500  -0.2566   0.03348   0.02676  -0.1108   0.9436   0.0447
  -6.250  -0.2176   0.03058   0.02340  -0.1153   0.9401   0.0469
  -6.000  -0.1842   0.02836   0.02074  -0.1179   0.9337   0.0501
  -5.750  -0.1461   0.02625   0.01808  -0.1209   0.9293   0.0531
  -5.500  -0.1071   0.02440   0.01586  -0.1236   0.9262   0.0550
  -5.250  -0.0750   0.02331   0.01475  -0.1251   0.9203   0.0583
  -5.000  -0.0400   0.02229   0.01359  -0.1268   0.9153   0.0617
  -4.750  -0.0021   0.02119   0.01231  -0.1288   0.9118   0.0647
  -4.500   0.0325   0.02031   0.01132  -0.1302   0.9068   0.0684
  -4.250   0.0654   0.01965   0.01071  -0.1314   0.9005   0.0735
  -4.000   0.1025   0.01895   0.00991  -0.1332   0.8962   0.0791
  -3.750   0.1380   0.01826   0.00923  -0.1349   0.8910   0.0856
  -3.500   0.1716   0.01775   0.00868  -0.1362   0.8841   0.0971
  -3.250   0.2103   0.01709   0.00804  -0.1386   0.8796   0.1161
  -3.000   0.2447   0.01650   0.00753  -0.1402   0.8727   0.1448
  -2.750   0.2818   0.01552   0.00723  -0.1429   0.8663   0.2896
  -2.500   0.3184   0.01514   0.00711  -0.1447   0.8604   0.4072
  -2.250   0.3476   0.01502   0.00715  -0.1447   0.8507   0.4623
  -2.000   0.3800   0.01496   0.00715  -0.1451   0.8431   0.5102
  -1.750   0.4091   0.01502   0.00721  -0.1449   0.8336   0.5509
  -1.500   0.4393   0.01505   0.00721  -0.1450   0.8256   0.5800
  -1.250   0.4682   0.01509   0.00722  -0.1448   0.8170   0.6050
  -1.000   0.4969   0.01513   0.00724  -0.1446   0.8089   0.6289
  -0.750   0.5253   0.01516   0.00724  -0.1443   0.8005   0.6494
  -0.500   0.5533   0.01520   0.00725  -0.1440   0.7922   0.6654
  -0.250   0.5821   0.01522   0.00723  -0.1439   0.7839   0.6805
   0.000   0.6090   0.01527   0.00727  -0.1434   0.7751   0.6947
   0.250   0.6375   0.01528   0.00725  -0.1432   0.7671   0.7087
   0.500   0.6636   0.01535   0.00733  -0.1426   0.7577   0.7224
   0.750   0.6924   0.01536   0.00730  -0.1424   0.7500   0.7364
   1.000   0.7177   0.01545   0.00742  -0.1418   0.7399   0.7504
   1.250   0.7452   0.01548   0.00745  -0.1414   0.7313   0.7644
   1.500   0.7712   0.01554   0.00753  -0.1408   0.7216   0.7787
   1.750   0.7969   0.01560   0.00762  -0.1401   0.7118   0.7935
   2.000   0.8235   0.01560   0.00764  -0.1394   0.7030   0.8090
   2.250   0.8470   0.01567   0.00778  -0.1383   0.6918   0.8259
   2.500   0.8708   0.01569   0.00784  -0.1372   0.6816   0.8450
   2.750   0.8943   0.01566   0.00786  -0.1359   0.6715   0.8690
   3.000   0.9142   0.01561   0.00789  -0.1339   0.6583   0.9082
   3.250   0.9410   0.01559   0.00787  -0.1335   0.6428   1.0000
   3.500   0.9703   0.01574   0.00799  -0.1337   0.6264   1.0000
   3.750   0.9989   0.01594   0.00815  -0.1339   0.6109   1.0000
   4.000   1.0270   0.01616   0.00836  -0.1339   0.5959   1.0000
   4.250   1.0545   0.01641   0.00861  -0.1338   0.5807   1.0000
   4.500   1.0816   0.01666   0.00887  -0.1336   0.5653   1.0000
   4.750   1.1082   0.01694   0.00915  -0.1333   0.5492   1.0000
   5.000   1.1341   0.01723   0.00943  -0.1329   0.5313   1.0000
   5.250   1.1587   0.01754   0.00973  -0.1322   0.5101   1.0000
   5.500   1.1825   0.01790   0.01003  -0.1314   0.4862   1.0000
   5.750   1.2051   0.01833   0.01037  -0.1304   0.4594   1.0000
   6.000   1.2273   0.01883   0.01080  -0.1294   0.4340   1.0000
   6.250   1.2493   0.01936   0.01129  -0.1284   0.4098   1.0000
   6.500   1.2703   0.01995   0.01183  -0.1273   0.3841   1.0000
   6.750   1.2895   0.02062   0.01242  -0.1260   0.3527   1.0000
   7.000   1.3065   0.02142   0.01309  -0.1244   0.3150   1.0000
   7.250   1.3218   0.02236   0.01383  -0.1226   0.2756   1.0000
   7.500   1.3359   0.02341   0.01469  -0.1207   0.2407   1.0000
   7.750   1.3500   0.02449   0.01565  -0.1189   0.2129   1.0000
   8.000   1.3636   0.02561   0.01667  -0.1170   0.1892   1.0000
   8.250   1.3765   0.02674   0.01778  -0.1151   0.1667   1.0000
   8.500   1.3867   0.02796   0.01893  -0.1129   0.1467   1.0000
   8.750   1.3962   0.02920   0.02014  -0.1105   0.1288   1.0000
   9.000   1.4042   0.03055   0.02146  -0.1081   0.1146   1.0000
   9.250   1.4110   0.03201   0.02290  -0.1057   0.1042   1.0000
   9.500   1.4169   0.03358   0.02447  -0.1033   0.0962   1.0000
   9.750   1.4233   0.03519   0.02618  -0.1011   0.0902   1.0000
  10.000   1.4286   0.03695   0.02800  -0.0990   0.0852   1.0000
  10.250   1.4315   0.03898   0.03004  -0.0970   0.0814   1.0000
  10.500   1.4390   0.04076   0.03197  -0.0953   0.0774   1.0000
  10.750   1.4449   0.04271   0.03403  -0.0938   0.0738   1.0000
  11.000   1.4488   0.04492   0.03626  -0.0923   0.0708   1.0000
  11.250   1.4550   0.04706   0.03850  -0.0910   0.0683   1.0000
  11.500   1.4634   0.04907   0.04071  -0.0898   0.0658   1.0000
  11.750   1.4708   0.05121   0.04298  -0.0887   0.0633   1.0000
  12.000   1.4770   0.05346   0.04533  -0.0878   0.0610   1.0000
  12.250   1.4822   0.05589   0.04780  -0.0869   0.0589   1.0000
  12.500   1.4891   0.05829   0.05035  -0.0860   0.0569   1.0000
  12.750   1.4951   0.06079   0.05309  -0.0853   0.0548   1.0000
  13.000   1.4988   0.06347   0.05596  -0.0848   0.0526   1.0000
  13.250   1.5012   0.06629   0.05891  -0.0844   0.0507   1.0000
  13.500   1.5033   0.06921   0.06190  -0.0842   0.0491   1.0000
  13.750   1.5056   0.07232   0.06515  -0.0839   0.0475   1.0000
  14.000   1.5036   0.07599   0.06914  -0.0840   0.0458   1.0000
  14.250   1.5012   0.07979   0.07318  -0.0843   0.0442   1.0000
  14.500   1.4985   0.08367   0.07725  -0.0849   0.0428   1.0000
  14.750   1.4954   0.08762   0.08134  -0.0857   0.0415   1.0000
  15.000   1.4931   0.09148   0.08527  -0.0866   0.0402   1.0000
  15.250   1.4904   0.09564   0.08953  -0.0876   0.0391   1.0000
  15.500   1.4797   0.10140   0.09563  -0.0897   0.0382   1.0000
  15.750   1.4680   0.10752   0.10206  -0.0922   0.0372   1.0000
  16.000   1.4557   0.11393   0.10873  -0.0953   0.0364   1.0000
  16.250   1.4428   0.12071   0.11576  -0.0989   0.0356   1.0000
  16.500   1.4293   0.12787   0.12313  -0.1030   0.0350   1.0000
  16.750   1.4151   0.13546   0.13093  -0.1077   0.0344   1.0000
  17.000   1.3992   0.14375   0.13942  -0.1132   0.0340   1.0000
  17.250   1.3682   0.15669   0.15265  -0.1223   0.0342   1.0000
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