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

WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)
Reynolds number: 100,000
Max Cl/Cd: 60.46 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx601261-il-100000-n5.txt
Download as CSV file: xf-fx601261-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 60-126/1 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3525   0.08601   0.08117  -0.0496   1.0000   0.0220
  -9.000  -0.3574   0.08224   0.07748  -0.0501   1.0000   0.0217
  -8.750  -0.3654   0.07813   0.07346  -0.0508   1.0000   0.0214
  -8.500  -0.3823   0.07315   0.06858  -0.0518   1.0000   0.0210
  -8.250  -0.4060   0.06922   0.06476  -0.0516   1.0000   0.0208
  -8.000  -0.4321   0.06461   0.06020  -0.0535   0.9966   0.0206
  -7.750  -0.4274   0.05242   0.04758  -0.0753   0.9778   0.0200
  -7.500  -0.4116   0.04518   0.03974  -0.0859   0.9656   0.0193
  -7.250  -0.3861   0.03931   0.03308  -0.0932   0.9573   0.0186
  -7.000  -0.3570   0.03560   0.02868  -0.0971   0.9493   0.0182
  -6.750  -0.3218   0.03296   0.02554  -0.1005   0.9447   0.0180
  -6.500  -0.2930   0.03076   0.02304  -0.1019   0.9371   0.0179
  -6.250  -0.2580   0.02872   0.02075  -0.1042   0.9327   0.0179
  -6.000  -0.2246   0.02704   0.01887  -0.1058   0.9276   0.0179
  -5.750  -0.1929   0.02566   0.01735  -0.1070   0.9213   0.0180
  -5.500  -0.1574   0.02431   0.01592  -0.1088   0.9170   0.0181
  -5.250  -0.1257   0.02314   0.01468  -0.1101   0.9106   0.0183
  -5.000  -0.0914   0.02209   0.01353  -0.1118   0.9043   0.0185
  -4.750  -0.0524   0.02105   0.01234  -0.1144   0.8999   0.0189
  -4.500  -0.0220   0.02031   0.01144  -0.1153   0.8910   0.0194
  -4.250   0.0157   0.01954   0.01048  -0.1175   0.8856   0.0201
  -4.000   0.0469   0.01900   0.00977  -0.1183   0.8775   0.0210
  -3.750   0.0820   0.01847   0.00908  -0.1197   0.8712   0.0222
  -3.500   0.1143   0.01793   0.00848  -0.1207   0.8639   0.0255
  -3.250   0.1485   0.01648   0.00772  -0.1232   0.8567   0.1613
  -3.000   0.1812   0.01575   0.00757  -0.1247   0.8494   0.3067
  -2.750   0.2118   0.01567   0.00764  -0.1251   0.8407   0.3818
  -2.500   0.2418   0.01577   0.00774  -0.1251   0.8318   0.4289
  -2.250   0.2722   0.01579   0.00769  -0.1252   0.8235   0.4507
  -2.000   0.2997   0.01597   0.00785  -0.1248   0.8144   0.4805
  -1.750   0.3299   0.01602   0.00783  -0.1248   0.8068   0.5000
  -1.500   0.3572   0.01603   0.00776  -0.1245   0.7974   0.5107
  -1.250   0.3880   0.01600   0.00759  -0.1247   0.7899   0.5229
  -1.000   0.4138   0.01601   0.00759  -0.1241   0.7792   0.5325
  -0.750   0.4422   0.01598   0.00748  -0.1239   0.7697   0.5420
  -0.500   0.4708   0.01594   0.00736  -0.1238   0.7600   0.5519
  -0.250   0.4974   0.01595   0.00736  -0.1233   0.7497   0.5608
   0.000   0.5266   0.01594   0.00727  -0.1233   0.7413   0.5716
   0.250   0.5532   0.01596   0.00729  -0.1229   0.7310   0.5818
   0.500   0.5804   0.01596   0.00729  -0.1225   0.7209   0.5920
   0.750   0.6090   0.01594   0.00721  -0.1223   0.7112   0.6030
   1.000   0.6351   0.01596   0.00724  -0.1218   0.6992   0.6131
   1.250   0.6618   0.01598   0.00727  -0.1214   0.6878   0.6231
   1.500   0.6897   0.01600   0.00726  -0.1211   0.6778   0.6344
   1.750   0.7167   0.01604   0.00732  -0.1207   0.6674   0.6463
   2.000   0.7430   0.01610   0.00742  -0.1202   0.6563   0.6585
   2.250   0.7695   0.01614   0.00748  -0.1197   0.6447   0.6723
   2.500   0.7961   0.01618   0.00753  -0.1192   0.6329   0.6876
   2.750   0.8216   0.01623   0.00763  -0.1185   0.6201   0.7042
   3.000   0.8468   0.01630   0.00775  -0.1177   0.6070   0.7226
   3.250   0.8716   0.01637   0.00790  -0.1169   0.5944   0.7442
   3.500   0.8956   0.01642   0.00803  -0.1159   0.5824   0.7708
   3.750   0.9177   0.01643   0.00813  -0.1144   0.5700   0.8075
   4.000   0.9358   0.01631   0.00816  -0.1120   0.5568   0.8879
   4.250   0.9628   0.01645   0.00828  -0.1118   0.5410   1.0000
   4.500   0.9888   0.01672   0.00848  -0.1114   0.5234   1.0000
   4.750   1.0140   0.01701   0.00872  -0.1110   0.5056   1.0000
   5.000   1.0391   0.01732   0.00900  -0.1105   0.4888   1.0000
   5.250   1.0636   0.01765   0.00929  -0.1099   0.4718   1.0000
   5.500   1.0877   0.01800   0.00963  -0.1092   0.4544   1.0000
   5.750   1.1113   0.01838   0.00998  -0.1085   0.4368   1.0000
   6.000   1.1341   0.01879   0.01035  -0.1077   0.4185   1.0000
   6.250   1.1561   0.01924   0.01076  -0.1067   0.3990   1.0000
   6.500   1.1774   0.01971   0.01123  -0.1057   0.3775   1.0000
   6.750   1.1974   0.02026   0.01170  -0.1045   0.3555   1.0000
   7.000   1.2168   0.02085   0.01225  -0.1032   0.3324   1.0000
   7.500   1.2523   0.02222   0.01349  -0.1003   0.2855   1.0000
   7.750   1.2684   0.02301   0.01420  -0.0987   0.2628   1.0000
   8.000   1.2841   0.02382   0.01498  -0.0971   0.2407   1.0000
   8.250   1.2983   0.02471   0.01582  -0.0953   0.2224   1.0000
   8.500   1.3125   0.02559   0.01670  -0.0936   0.2056   1.0000
   8.750   1.3243   0.02651   0.01762  -0.0914   0.1915   1.0000
   9.000   1.3349   0.02752   0.01863  -0.0892   0.1793   1.0000
   9.250   1.3449   0.02859   0.01972  -0.0871   0.1682   1.0000
   9.500   1.3538   0.02975   0.02090  -0.0849   0.1577   1.0000
   9.750   1.3635   0.03090   0.02212  -0.0830   0.1476   1.0000
  10.000   1.3718   0.03218   0.02345  -0.0810   0.1398   1.0000
  10.250   1.3783   0.03362   0.02494  -0.0791   0.1333   1.0000
  10.500   1.3859   0.03508   0.02648  -0.0774   0.1266   1.0000
  10.750   1.3916   0.03671   0.02817  -0.0757   0.1193   1.0000
  11.000   1.3983   0.03834   0.02989  -0.0743   0.1116   1.0000
  11.250   1.4023   0.04022   0.03182  -0.0730   0.1044   1.0000
  11.500   1.4079   0.04206   0.03376  -0.0718   0.0977   1.0000
  11.750   1.4097   0.04430   0.03602  -0.0707   0.0927   1.0000
  12.000   1.4141   0.04641   0.03827  -0.0698   0.0884   1.0000
  12.250   1.4186   0.04859   0.04061  -0.0690   0.0842   1.0000
  12.500   1.4201   0.05112   0.04324  -0.0683   0.0808   1.0000
  12.750   1.4215   0.05375   0.04598  -0.0678   0.0773   1.0000
  13.000   1.4256   0.05620   0.04863  -0.0675   0.0730   1.0000
  13.250   1.4259   0.05911   0.05168  -0.0674   0.0692   1.0000
  13.500   1.4254   0.06222   0.05489  -0.0674   0.0663   1.0000
  13.750   1.4255   0.06537   0.05820  -0.0676   0.0637   1.0000
  14.000   1.4240   0.06881   0.06180  -0.0679   0.0618   1.0000
  14.250   1.4212   0.07253   0.06564  -0.0686   0.0602   1.0000
  14.500   1.4175   0.07651   0.06973  -0.0694   0.0588   1.0000
  14.750   1.4131   0.08069   0.07398  -0.0704   0.0575   1.0000
  15.000   1.4124   0.08448   0.07800  -0.0713   0.0560   1.0000
  15.250   1.4102   0.08860   0.08233  -0.0724   0.0544   1.0000
  15.500   1.4068   0.09300   0.08692  -0.0738   0.0529   1.0000
  15.750   1.4019   0.09775   0.09185  -0.0756   0.0513   1.0000
  16.000   1.3954   0.10288   0.09714  -0.0778   0.0498   1.0000
  16.250   1.3878   0.10833   0.10271  -0.0803   0.0485   1.0000
  16.500   1.3803   0.11389   0.10839  -0.0829   0.0472   1.0000
  16.750   1.3730   0.11967   0.11443  -0.0858   0.0455   1.0000
  17.000   1.3643   0.12580   0.12079  -0.0890   0.0441   1.0000
  17.250   1.3544   0.13233   0.12753  -0.0926   0.0427   1.0000
  17.500   1.3440   0.13909   0.13446  -0.0965   0.0418   1.0000
  17.750   1.3331   0.14615   0.14169  -0.1008   0.0410   1.0000
  18.000   1.3219   0.15341   0.14910  -0.1053   0.0402   1.0000
  18.250   1.3112   0.16068   0.15649  -0.1100   0.0394   1.0000
  18.500   1.2968   0.16918   0.16514  -0.1155   0.0389   1.0000
  18.750   1.2752   0.18001   0.17614  -0.1227   0.0386   1.0000
  19.000   1.2494   0.19274   0.18897  -0.1310   0.0389   1.0000
  19.250   1.2193   0.20825   0.20448  -0.1407   0.0390   1.0000
<< Back to WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)