Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 60-160 AIRFOIL (fx60160-il)
Reynolds number: 200,000
Max Cl/Cd: 68.16 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60160-il-200000-n5.txt
Download as CSV file: xf-fx60160-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-160 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5417   0.07651   0.07269  -0.0755   1.0000   0.0264
 -12.250  -0.5809   0.06887   0.06496  -0.0788   1.0000   0.0263
 -12.000  -0.6130   0.06208   0.05800  -0.0825   0.9986   0.0262
 -11.750  -0.6444   0.05320   0.04868  -0.0906   0.9914   0.0265
 -11.500  -0.6512   0.04841   0.04361  -0.0952   0.9848   0.0269
 -11.250  -0.6432   0.04606   0.04116  -0.0976   0.9779   0.0273
 -11.000  -0.6305   0.04381   0.03877  -0.1006   0.9722   0.0277
 -10.750  -0.6196   0.04232   0.03716  -0.1015   0.9633   0.0283
 -10.500  -0.6004   0.03992   0.03455  -0.1042   0.9589   0.0291
 -10.250  -0.5919   0.03763   0.03200  -0.1041   0.9494   0.0297
 -10.000  -0.5715   0.03492   0.02894  -0.1061   0.9451   0.0308
  -9.750  -0.5594   0.03287   0.02655  -0.1055   0.9351   0.0318
  -9.500  -0.5358   0.03085   0.02409  -0.1068   0.9302   0.0328
  -9.250  -0.5193   0.02912   0.02220  -0.1060   0.9206   0.0334
  -8.750  -0.4706   0.02670   0.01958  -0.1069   0.9064   0.0349
  -8.500  -0.4423   0.02567   0.01841  -0.1079   0.9005   0.0359
  -8.250  -0.4189   0.02479   0.01740  -0.1077   0.8916   0.0371
  -8.000  -0.3895   0.02375   0.01619  -0.1087   0.8858   0.0384
  -7.750  -0.3639   0.02278   0.01506  -0.1087   0.8776   0.0394
  -7.500  -0.3342   0.02186   0.01398  -0.1095   0.8712   0.0403
  -7.250  -0.3079   0.02098   0.01300  -0.1096   0.8634   0.0411
  -7.000  -0.2804   0.02005   0.01205  -0.1101   0.8568   0.0426
  -6.750  -0.2547   0.01944   0.01141  -0.1102   0.8491   0.0441
  -6.500  -0.2276   0.01883   0.01073  -0.1105   0.8421   0.0457
  -6.250  -0.2026   0.01824   0.01007  -0.1103   0.8347   0.0471
  -6.000  -0.1771   0.01770   0.00944  -0.1103   0.8279   0.0487
  -5.750  -0.1518   0.01725   0.00889  -0.1102   0.8215   0.0500
  -5.500  -0.1293   0.01663   0.00825  -0.1097   0.8144   0.0521
  -5.250  -0.1038   0.01613   0.00769  -0.1098   0.8089   0.0547
  -5.000  -0.0809   0.01575   0.00728  -0.1093   0.8021   0.0572
  -4.750  -0.0556   0.01539   0.00682  -0.1092   0.7964   0.0599
  -4.500  -0.0300   0.01505   0.00639  -0.1091   0.7911   0.0625
  -4.250  -0.0065   0.01465   0.00599  -0.1088   0.7849   0.0677
  -4.000   0.0198   0.01438   0.00563  -0.1088   0.7799   0.0737
  -3.750   0.0455   0.01405   0.00529  -0.1088   0.7750   0.0836
  -3.500   0.0692   0.01364   0.00503  -0.1085   0.7693   0.1155
  -3.250   0.0882   0.01236   0.00453  -0.1082   0.7642   0.3203
  -3.000   0.1103   0.01171   0.00444  -0.1077   0.7598   0.4629
  -2.750   0.1342   0.01164   0.00461  -0.1069   0.7542   0.5289
  -2.500   0.1608   0.01173   0.00474  -0.1065   0.7494   0.5643
  -2.250   0.1894   0.01184   0.00478  -0.1066   0.7453   0.5868
  -2.000   0.2152   0.01198   0.00491  -0.1061   0.7399   0.6049
  -1.750   0.2422   0.01211   0.00499  -0.1059   0.7347   0.6196
  -1.500   0.2702   0.01228   0.00509  -0.1057   0.7303   0.6321
  -1.250   0.2965   0.01244   0.00525  -0.1053   0.7253   0.6423
  -1.000   0.3231   0.01254   0.00528  -0.1051   0.7197   0.6512
  -0.750   0.3508   0.01262   0.00533  -0.1050   0.7151   0.6562
  -0.500   0.3782   0.01267   0.00532  -0.1050   0.7103   0.6607
  -0.250   0.4046   0.01271   0.00532  -0.1048   0.7047   0.6663
   0.000   0.4317   0.01279   0.00539  -0.1046   0.6999   0.6709
   0.250   0.4592   0.01288   0.00544  -0.1046   0.6953   0.6769
   0.500   0.4850   0.01294   0.00549  -0.1043   0.6895   0.6824
   0.750   0.5118   0.01299   0.00554  -0.1041   0.6846   0.6859
   1.000   0.5393   0.01304   0.00556  -0.1041   0.6799   0.6896
   1.250   0.5649   0.01309   0.00562  -0.1038   0.6739   0.6936
   1.500   0.5922   0.01313   0.00562  -0.1038   0.6687   0.6973
   1.750   0.6190   0.01317   0.00568  -0.1036   0.6636   0.6999
   2.000   0.6441   0.01323   0.00578  -0.1032   0.6575   0.7029
   2.250   0.6711   0.01328   0.00582  -0.1031   0.6521   0.7063
   2.500   0.6973   0.01334   0.00589  -0.1029   0.6464   0.7099
   2.750   0.7229   0.01341   0.00598  -0.1026   0.6401   0.7132
   3.000   0.7499   0.01346   0.00603  -0.1025   0.6349   0.7158
   3.250   0.7740   0.01353   0.00619  -0.1019   0.6280   0.7186
   3.500   0.7999   0.01360   0.00628  -0.1016   0.6217   0.7217
   3.750   0.8252   0.01368   0.00639  -0.1012   0.6148   0.7252
   4.000   0.8499   0.01375   0.00646  -0.1007   0.6061   0.7286
   4.250   0.8726   0.01380   0.00658  -0.0998   0.5953   0.7310
   4.500   0.8957   0.01387   0.00666  -0.0989   0.5844   0.7338
   4.750   0.9177   0.01394   0.00674  -0.0977   0.5710   0.7371
   5.000   0.9377   0.01404   0.00684  -0.0963   0.5540   0.7405
   5.500   0.9746   0.01435   0.00707  -0.0928   0.5141   0.7465
   5.750   0.9924   0.01456   0.00726  -0.0909   0.4958   0.7495
   6.000   1.0089   0.01481   0.00749  -0.0889   0.4750   0.7529
   6.250   1.0216   0.01514   0.00773  -0.0862   0.4509   0.7564
   6.500   1.0314   0.01553   0.00802  -0.0829   0.4243   0.7599
   6.750   1.0382   0.01603   0.00843  -0.0793   0.3948   0.7630
   7.000   1.0437   0.01667   0.00894  -0.0755   0.3617   0.7666
   7.250   1.0438   0.01757   0.00964  -0.0711   0.3166   0.7704
   7.500   1.0394   0.01878   0.01054  -0.0663   0.2588   0.7745
   7.750   1.0298   0.02036   0.01177  -0.0611   0.1940   0.7782
   8.000   1.0118   0.02265   0.01355  -0.0555   0.1059   0.7824
   8.250   1.0137   0.02404   0.01481  -0.0525   0.0854   0.7867
   8.500   1.0227   0.02511   0.01589  -0.0506   0.0772   0.7908
   8.750   1.0322   0.02617   0.01702  -0.0488   0.0715   0.7949
   9.000   1.0405   0.02738   0.01829  -0.0471   0.0671   0.7999
   9.250   1.0523   0.02840   0.01941  -0.0458   0.0641   0.8052
   9.500   1.0627   0.02955   0.02066  -0.0444   0.0613   0.8102
   9.750   1.0715   0.03086   0.02204  -0.0431   0.0589   0.8162
  10.000   1.0783   0.03236   0.02362  -0.0417   0.0572   0.8230
  10.250   1.0858   0.03387   0.02524  -0.0405   0.0556   0.8318
  10.500   1.0955   0.03525   0.02677  -0.0395   0.0545   0.8429
  10.750   1.1053   0.03670   0.02839  -0.0387   0.0534   0.8601
  11.000   1.1182   0.03818   0.03009  -0.0389   0.0523   0.9363
  11.250   1.1227   0.03971   0.03168  -0.0373   0.0514   1.0000
  11.500   1.1310   0.04138   0.03340  -0.0364   0.0504   1.0000
  11.750   1.1394   0.04306   0.03514  -0.0357   0.0494   1.0000
  12.000   1.1475   0.04479   0.03691  -0.0350   0.0483   1.0000
  12.250   1.1546   0.04663   0.03876  -0.0343   0.0470   1.0000
  12.500   1.1623   0.04844   0.04060  -0.0336   0.0458   1.0000
  12.750   1.1734   0.04997   0.04224  -0.0332   0.0445   1.0000
  13.000   1.1836   0.05161   0.04397  -0.0328   0.0431   1.0000
  13.250   1.1931   0.05334   0.04578  -0.0324   0.0416   1.0000
  13.500   1.2020   0.05514   0.04766  -0.0321   0.0405   1.0000
  13.750   1.2100   0.05706   0.04964  -0.0319   0.0391   1.0000
  14.000   1.2167   0.05915   0.05176  -0.0316   0.0379   1.0000
  14.250   1.2243   0.06115   0.05381  -0.0313   0.0368   1.0000
  14.500   1.2332   0.06308   0.05589  -0.0312   0.0357   1.0000
  14.750   1.2413   0.06513   0.05807  -0.0312   0.0343   1.0000
  15.000   1.2482   0.06735   0.06039  -0.0313   0.0328   1.0000
  15.250   1.2542   0.06972   0.06286  -0.0315   0.0316   1.0000
  15.500   1.2587   0.07232   0.06552  -0.0319   0.0304   1.0000
  15.750   1.2626   0.07499   0.06825  -0.0321   0.0292   1.0000
  16.000   1.2694   0.07738   0.07083  -0.0324   0.0278   1.0000
  16.250   1.2745   0.08002   0.07361  -0.0328   0.0263   1.0000
  16.500   1.2780   0.08293   0.07662  -0.0335   0.0249   1.0000
  16.750   1.2798   0.08615   0.07990  -0.0343   0.0238   1.0000
  17.000   1.2834   0.08908   0.08300  -0.0349   0.0222   1.0000
  17.250   1.2864   0.09219   0.08625  -0.0357   0.0204   1.0000
  17.500   1.2879   0.09557   0.08974  -0.0368   0.0193   1.0000
  17.750   1.2888   0.09904   0.09331  -0.0379   0.0182   1.0000
  18.000   1.2896   0.10252   0.09694  -0.0389   0.0168   1.0000
  18.250   1.2897   0.10621   0.10074  -0.0402   0.0158   1.0000
  18.500   1.2888   0.11012   0.10474  -0.0419   0.0151   1.0000
  18.750   1.2866   0.11425   0.10898  -0.0435   0.0145   1.0000
  19.000   1.2839   0.11850   0.11337  -0.0452   0.0139   1.0000
  19.250   1.2802   0.12295   0.11796  -0.0472   0.0135   1.0000
<< Back to FX 60-160 AIRFOIL (fx60160-il)

Polar data table (+)

Polar graphs


<< Back to FX 60-160 AIRFOIL (fx60160-il)