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WORTMANN FX 76-120 (fx76120-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 76-120 (fx76120-il)
Reynolds number: 100,000
Max Cl/Cd: 35.9 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76120-il-100000.txt
Download as CSV file: xf-fx76120-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 76-120                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.8039   0.08399   0.07831  -0.0358   1.0000   0.0832
 -12.500  -0.8351   0.07551   0.06977  -0.0406   1.0000   0.0823
 -12.250  -0.8724   0.06808   0.06220  -0.0441   1.0000   0.0814
 -12.000  -0.9071   0.06243   0.05637  -0.0450   1.0000   0.0808
 -11.750  -0.9358   0.05812   0.05185  -0.0436   1.0000   0.0802
 -11.500  -0.9627   0.05463   0.04813  -0.0401   1.0000   0.0802
 -11.250  -0.9827   0.05153   0.04474  -0.0363   1.0000   0.0809
 -11.000  -0.9970   0.04840   0.04123  -0.0326   1.0000   0.0818
 -10.750  -1.0069   0.04564   0.03802  -0.0288   1.0000   0.0830
 -10.500  -1.0051   0.04255   0.03468  -0.0263   1.0000   0.0848
 -10.250  -0.9918   0.04044   0.03252  -0.0248   1.0000   0.0872
 -10.000  -0.9804   0.03863   0.03056  -0.0228   1.0000   0.0901
  -9.750  -0.9724   0.03676   0.02836  -0.0202   1.0000   0.0936
  -9.500  -0.9637   0.03467   0.02589  -0.0175   1.0000   0.0966
  -9.250  -0.9441   0.03296   0.02430  -0.0165   1.0000   0.1008
  -9.000  -0.9295   0.03158   0.02270  -0.0145   1.0000   0.1058
  -8.750  -0.9138   0.02990   0.02083  -0.0126   1.0000   0.1109
  -8.500  -0.8951   0.02873   0.01973  -0.0112   1.0000   0.1171
  -8.250  -0.8787   0.02738   0.01817  -0.0092   1.0000   0.1243
  -8.000  -0.8608   0.02642   0.01730  -0.0076   1.0000   0.1329
  -7.750  -0.8433   0.02530   0.01619  -0.0059   1.0000   0.1426
  -7.500  -0.8268   0.02434   0.01519  -0.0039   1.0000   0.1546
  -7.250  -0.8104   0.02348   0.01433  -0.0018   1.0000   0.1687
  -7.000  -0.7944   0.02271   0.01362   0.0002   1.0000   0.1848
  -6.750  -0.7784   0.02202   0.01299   0.0023   1.0000   0.2022
  -6.500  -0.7624   0.02140   0.01243   0.0045   1.0000   0.2206
  -6.250  -0.7461   0.02084   0.01189   0.0066   1.0000   0.2395
  -6.000  -0.7296   0.02033   0.01137   0.0086   1.0000   0.2585
  -5.750  -0.7127   0.01986   0.01087   0.0106   1.0000   0.2770
  -5.500  -0.6950   0.01936   0.01043   0.0125   1.0000   0.2949
  -5.250  -0.6769   0.01888   0.01003   0.0143   1.0000   0.3129
  -5.000  -0.6587   0.01843   0.00965   0.0160   1.0000   0.3310
  -4.750  -0.6402   0.01799   0.00928   0.0178   1.0000   0.3497
  -4.500  -0.6218   0.01758   0.00894   0.0195   1.0000   0.3696
  -4.250  -0.6033   0.01718   0.00859   0.0213   1.0000   0.3911
  -4.000  -0.5846   0.01676   0.00829   0.0230   1.0000   0.4132
  -3.750  -0.5661   0.01637   0.00803   0.0247   1.0000   0.4381
  -3.500  -0.5476   0.01597   0.00780   0.0264   1.0000   0.4654
  -3.250  -0.5296   0.01560   0.00761   0.0283   1.0000   0.4969
  -3.000  -0.5120   0.01526   0.00749   0.0303   1.0000   0.5330
  -2.750  -0.4950   0.01496   0.00740   0.0325   1.0000   0.5754
  -2.500  -0.4781   0.01468   0.00741   0.0347   1.0000   0.6218
  -2.250  -0.4610   0.01449   0.00749   0.0371   1.0000   0.6729
  -2.000  -0.4431   0.01441   0.00765   0.0395   1.0000   0.7277
  -1.750  -0.4222   0.01449   0.00794   0.0415   1.0000   0.7811
  -1.500  -0.3964   0.01474   0.00832   0.0425   1.0000   0.8320
  -1.250  -0.3642   0.01514   0.00877   0.0423   1.0000   0.8786
  -1.000  -0.3148   0.01576   0.00937   0.0387   1.0000   0.9142
  -0.750  -0.2553   0.01646   0.01001   0.0328   1.0000   0.9410
  -0.500  -0.1795   0.01716   0.01063   0.0237   0.9974   0.9577
  -0.250  -0.0903   0.01768   0.01110   0.0120   0.9889   0.9694
   0.000   0.0003   0.01787   0.01127  -0.0001   0.9802   0.9802
   0.250   0.0898   0.01769   0.01111  -0.0119   0.9695   0.9889
   0.500   0.1794   0.01716   0.01064  -0.0237   0.9576   0.9972
   0.750   0.2553   0.01646   0.01000  -0.0329   0.9410   1.0000
   1.000   0.3143   0.01577   0.00938  -0.0386   0.9145   1.0000
   1.250   0.3640   0.01514   0.00877  -0.0423   0.8787   1.0000
   1.500   0.3963   0.01474   0.00832  -0.0426   0.8321   1.0000
   1.750   0.4222   0.01449   0.00793  -0.0414   0.7808   1.0000
   2.000   0.4431   0.01441   0.00764  -0.0395   0.7274   1.0000
   2.250   0.4609   0.01449   0.00748  -0.0371   0.6727   1.0000
   2.500   0.4780   0.01468   0.00741  -0.0347   0.6215   1.0000
   2.750   0.4950   0.01495   0.00740  -0.0324   0.5753   1.0000
   3.000   0.5120   0.01526   0.00748  -0.0303   0.5329   1.0000
   3.250   0.5296   0.01560   0.00761  -0.0283   0.4971   1.0000
   3.500   0.5476   0.01597   0.00780  -0.0265   0.4656   1.0000
   3.750   0.5660   0.01636   0.00803  -0.0247   0.4382   1.0000
   4.000   0.5846   0.01675   0.00829  -0.0230   0.4133   1.0000
   4.250   0.6033   0.01718   0.00859  -0.0213   0.3912   1.0000
   4.500   0.6218   0.01758   0.00894  -0.0195   0.3697   1.0000
   4.750   0.6402   0.01799   0.00929  -0.0178   0.3498   1.0000
   5.000   0.6586   0.01843   0.00964  -0.0160   0.3311   1.0000
   5.250   0.6770   0.01888   0.01004  -0.0143   0.3130   1.0000
   5.500   0.6950   0.01936   0.01043  -0.0125   0.2950   1.0000
   5.750   0.7127   0.01985   0.01086  -0.0106   0.2771   1.0000
   6.000   0.7296   0.02033   0.01137  -0.0086   0.2586   1.0000
   6.250   0.7461   0.02084   0.01189  -0.0066   0.2396   1.0000
   6.500   0.7625   0.02141   0.01244  -0.0045   0.2209   1.0000
   6.750   0.7784   0.02202   0.01299  -0.0023   0.2022   1.0000
   7.000   0.7944   0.02271   0.01362  -0.0002   0.1847   1.0000
   7.250   0.8104   0.02348   0.01432   0.0018   0.1687   1.0000
   7.500   0.8268   0.02433   0.01518   0.0039   0.1547   1.0000
   7.750   0.8433   0.02529   0.01617   0.0059   0.1425   1.0000
   8.000   0.8609   0.02642   0.01728   0.0076   0.1330   1.0000
   8.250   0.8788   0.02738   0.01819   0.0092   0.1244   1.0000
   8.500   0.8952   0.02873   0.01973   0.0112   0.1171   1.0000
   8.750   0.9138   0.02989   0.02083   0.0126   0.1109   1.0000
   9.000   0.9294   0.03157   0.02270   0.0145   0.1057   1.0000
   9.250   0.9441   0.03292   0.02424   0.0165   0.1006   1.0000
   9.500   0.9638   0.03467   0.02588   0.0175   0.0966   1.0000
   9.750   0.9723   0.03674   0.02835   0.0202   0.0935   1.0000
  10.000   0.9804   0.03866   0.03059   0.0228   0.0902   1.0000
  10.250   0.9919   0.04045   0.03252   0.0248   0.0872   1.0000
  10.500   1.0064   0.04258   0.03466   0.0261   0.0845   1.0000
  10.750   1.0069   0.04562   0.03801   0.0288   0.0829   1.0000
  11.000   0.9967   0.04840   0.04124   0.0327   0.0817   1.0000
  11.250   0.9832   0.05149   0.04470   0.0363   0.0808   1.0000
  11.500   0.9625   0.05462   0.04812   0.0401   0.0801   1.0000
  11.750   0.9369   0.05811   0.05184   0.0435   0.0803   1.0000
  12.000   0.9059   0.06248   0.05643   0.0450   0.0806   1.0000
  12.250   0.8707   0.06821   0.06233   0.0439   0.0812   1.0000
  12.500   0.8340   0.07573   0.06999   0.0402   0.0823   1.0000
  12.750   0.8038   0.08414   0.07847   0.0355   0.0832   1.0000
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