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WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=50,000 Ncrit=0


Details Polar file
Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il)
Reynolds number: 50,000
Max Cl/Cd: 30.52 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx62k131-il-50000.txt
Download as CSV file: xf-fx62k131-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 62-K-131 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3388   0.13766   0.13118  -0.0419   1.0001   0.1693
 -10.500  -0.3536   0.13724   0.13087  -0.0403   1.0001   0.1748
 -10.250  -0.3786   0.13788   0.13166  -0.0392   1.0001   0.1764
 -10.000  -0.3610   0.13317   0.12694  -0.0362   1.0001   0.1875
  -9.750  -0.3861   0.13357   0.12749  -0.0352   1.0001   0.1904
  -9.500  -0.3725   0.12951   0.12344  -0.0325   1.0001   0.2012
  -9.250  -0.3991   0.12984   0.12391  -0.0315   1.0001   0.2046
  -9.000  -0.3871   0.12606   0.12015  -0.0289   1.0001   0.2165
  -8.750  -0.3897   0.12361   0.11777  -0.0270   1.0001   0.2242
  -8.500  -0.4087   0.12310   0.11737  -0.0255   1.0001   0.2325
  -8.250  -0.4023   0.11999   0.11429  -0.0232   1.0001   0.2442
  -8.000  -0.4051   0.11764   0.11201  -0.0212   1.0001   0.2540
  -7.750  -0.4352   0.11780   0.11231  -0.0195   1.0001   0.2616
  -7.500  -0.4333   0.11516   0.10971  -0.0171   1.0001   0.2753
  -7.250  -0.4347   0.11281   0.10742  -0.0147   1.0001   0.2892
  -7.000  -0.4400   0.11081   0.10549  -0.0122   1.0001   0.3034
  -6.750  -0.4491   0.10911   0.10388  -0.0095   1.0001   0.3181
  -6.500  -0.4379   0.10584   0.10063  -0.0069   1.0001   0.3374
  -6.250  -0.4397   0.10394   0.09873  -0.0039   1.0001   0.3580
  -6.000  -0.4606   0.10321   0.09812  -0.0002   1.0001   0.3754
  -5.750  -0.4484   0.10036   0.09529   0.0028   1.0001   0.4026
  -5.500  -0.4411   0.09791   0.09288   0.0059   1.0001   0.4300
  -5.250  -0.4384   0.09588   0.09089   0.0093   1.0001   0.4589
  -5.000  -0.4414   0.09435   0.08943   0.0134   1.0001   0.4892
  -4.750  -0.4211   0.09114   0.08622   0.0156   1.0001   0.5228
  -3.750  -0.3485   0.04876   0.04065  -0.0694   1.0001   0.1178
  -3.500  -0.3047   0.04545   0.03645  -0.0729   1.0001   0.1048
  -3.250  -0.2706   0.04291   0.03350  -0.0749   1.0001   0.1037
  -3.000  -0.2370   0.04113   0.03122  -0.0763   1.0001   0.1049
  -2.750  -0.2069   0.03957   0.02930  -0.0768   1.0001   0.1053
  -2.500  -0.1810   0.03822   0.02777  -0.0761   1.0001   0.1066
  -2.250  -0.1608   0.03720   0.02681  -0.0742   1.0001   0.1110
  -2.000  -0.1404   0.03662   0.02617  -0.0725   1.0001   0.1222
  -1.750  -0.1146   0.03596   0.02554  -0.0720   1.0001   0.1390
  -1.500  -0.0657   0.03355   0.02644  -0.0743   1.0001   0.6639
  -1.250  -0.0918   0.03500   0.02790  -0.0596   1.0001   0.7942
  -1.000  -0.1159   0.03526   0.02812  -0.0464   1.0001   0.8563
  -0.750  -0.1393   0.03467   0.02748  -0.0343   1.0001   0.9102
  -0.500  -0.1570   0.03305   0.02581  -0.0242   1.0001   0.9788
  -0.250  -0.1515   0.03207   0.02458  -0.0221   1.0001   0.9999
   0.000  -0.1275   0.03255   0.02464  -0.0237   1.0001   0.9999
   0.250  -0.1018   0.03318   0.02491  -0.0257   1.0001   0.9999
   0.500  -0.0749   0.03393   0.02531  -0.0279   1.0001   0.9999
   0.750  -0.0477   0.03477   0.02589  -0.0303   1.0001   0.9999
   1.000  -0.0202   0.03571   0.02658  -0.0327   1.0001   0.9999
   1.250   0.0073   0.03672   0.02738  -0.0351   1.0001   0.9999
   1.500   0.0346   0.03780   0.02829  -0.0375   1.0001   0.9999
   1.750   0.0615   0.03895   0.02925  -0.0399   1.0001   0.9999
   2.000   0.0880   0.04016   0.03033  -0.0423   1.0001   0.9999
   2.250   0.1144   0.04144   0.03150  -0.0446   1.0001   0.9999
   2.500   0.1400   0.04278   0.03275  -0.0469   1.0001   0.9999
   2.750   0.1650   0.04418   0.03405  -0.0491   1.0001   0.9999
   3.000   0.1896   0.04564   0.03546  -0.0513   1.0001   0.9999
   3.250   0.2137   0.04718   0.03696  -0.0535   1.0001   0.9999
   3.500   0.2373   0.04878   0.03854  -0.0557   1.0001   0.9999
   3.750   0.2606   0.05047   0.04021  -0.0578   1.0001   0.9999
   4.000   0.2829   0.05221   0.04195  -0.0599   1.0001   0.9999
   4.250   0.3189   0.05474   0.04450  -0.0646   0.9915   0.9999
   4.500   0.3581   0.05749   0.04729  -0.0699   0.9779   0.9999
   4.750   0.4012   0.06051   0.05035  -0.0757   0.9623   0.9999
   5.000   0.4319   0.06283   0.05272  -0.0792   0.9465   0.9999
   5.250   0.4601   0.06473   0.05471  -0.0819   0.9256   0.9999
   5.500   0.4984   0.06743   0.05751  -0.0862   0.9057   0.9999
   5.750   0.6149   0.06620   0.05637  -0.0939   0.7944   0.9999
   6.000   0.6346   0.06757   0.05790  -0.0944   0.7770   0.9999
   6.250   0.6615   0.06901   0.05948  -0.0958   0.7601   0.9999
   6.500   0.6942   0.07036   0.06099  -0.0976   0.7432   0.9999
   6.750   0.7320   0.07158   0.06239  -0.0998   0.7269   0.9999
   7.000   0.7544   0.07301   0.06404  -0.1005   0.7103   0.9999
   7.250   0.7735   0.07450   0.06571  -0.1008   0.6935   0.9999
   7.500   0.7998   0.07577   0.06719  -0.1017   0.6765   0.9999
   7.750   0.8363   0.07647   0.06815  -0.1030   0.6593   0.9999
   8.000   0.8652   0.07722   0.06919  -0.1034   0.6410   0.9999
   8.250   0.8870   0.07817   0.07038  -0.1032   0.6212   0.9999
   8.500   0.9472   0.07603   0.06866  -0.1040   0.6015   0.9999
   8.750   0.9596   0.07707   0.06994  -0.1027   0.5786   0.9999
   9.000   1.0069   0.07450   0.06786  -0.1015   0.5548   0.9999
   9.250   1.0940   0.06542   0.05954  -0.0986   0.5282   0.9999
   9.500   1.2439   0.04076   0.03586  -0.0878   0.4430   0.9999
   9.750   1.2377   0.04118   0.03560  -0.0816   0.3459   0.9999
  10.000   1.2190   0.04450   0.03802  -0.0767   0.2669   0.9999
  10.250   1.2050   0.04828   0.04101  -0.0730   0.2100   0.9999
  10.500   1.2111   0.05159   0.04362  -0.0698   0.1571   0.9999
  10.750   1.2417   0.05464   0.04618  -0.0678   0.1118   0.9999
  11.000   1.2675   0.05810   0.04951  -0.0670   0.0863   0.9999
  11.250   1.2982   0.06203   0.05365  -0.0666   0.0730   0.9999
  11.500   1.3435   0.06760   0.05927  -0.0682   0.0641   0.9999
  11.750   1.3447   0.07172   0.06393  -0.0660   0.0634   0.9999
  12.000   1.3406   0.07605   0.06874  -0.0638   0.0630   0.9999
  12.250   1.3326   0.08050   0.07359  -0.0619   0.0630   0.9999
  12.500   1.3205   0.08512   0.07857  -0.0601   0.0631   0.9999
  12.750   1.3067   0.08993   0.08369  -0.0588   0.0633   0.9999
  13.000   1.2922   0.09500   0.08903  -0.0580   0.0637   0.9999
  13.250   1.2781   0.10040   0.09468  -0.0577   0.0640   0.9999
  13.500   1.2578   0.10534   0.09993  -0.0579   0.0646   0.9999
  13.750   1.2112   0.11109   0.10611  -0.0602   0.0660   0.9999
  14.000   1.1614   0.12014   0.11553  -0.0657   0.0683   0.9999
  14.250   1.1265   0.13025   0.12582  -0.0725   0.0706   0.9999
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