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 76-100 (fx76100-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 76-100 (fx76100-il)
Reynolds number: 500,000
Max Cl/Cd: 62.87 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76100-il-500000.txt
Download as CSV file: xf-fx76100-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 76-100                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.9311   0.10389   0.10113  -0.0041   1.0000   0.0155
 -15.250  -0.9741   0.09082   0.08789  -0.0120   1.0000   0.0152
 -15.000  -1.0060   0.08044   0.07735  -0.0186   1.0000   0.0150
 -14.750  -1.0316   0.07132   0.06805  -0.0250   1.0000   0.0152
 -14.500  -1.0540   0.06350   0.06004  -0.0302   1.0000   0.0149
 -14.250  -1.0677   0.05742   0.05378  -0.0346   1.0000   0.0152
 -14.000  -1.0826   0.05179   0.04797  -0.0378   1.0000   0.0149
 -13.750  -1.0970   0.04676   0.04272  -0.0403   1.0000   0.0151
 -13.500  -1.1049   0.04312   0.03888  -0.0413   1.0000   0.0153
 -13.250  -1.1091   0.04032   0.03590  -0.0414   1.0000   0.0154
 -13.000  -1.1077   0.03855   0.03396  -0.0408   1.0000   0.0157
 -12.750  -1.1131   0.03593   0.03114  -0.0392   1.0000   0.0157
 -12.500  -1.1258   0.03259   0.02759  -0.0365   1.0000   0.0162
 -12.250  -1.1246   0.03089   0.02580  -0.0340   1.0000   0.0166
 -12.000  -1.1202   0.02960   0.02440  -0.0314   1.0000   0.0168
 -11.750  -1.1122   0.02876   0.02353  -0.0289   1.0000   0.0174
 -11.500  -1.1022   0.02764   0.02230  -0.0268   1.0000   0.0178
 -11.250  -1.0907   0.02653   0.02108  -0.0248   1.0000   0.0183
 -11.000  -1.0774   0.02555   0.01998  -0.0229   1.0000   0.0190
 -10.750  -1.0638   0.02445   0.01874  -0.0209   1.0000   0.0195
 -10.500  -1.0472   0.02375   0.01789  -0.0193   1.0000   0.0200
 -10.250  -1.0388   0.02185   0.01589  -0.0167   1.0000   0.0211
 -10.000  -1.0228   0.02101   0.01501  -0.0150   1.0000   0.0218
  -9.750  -1.0050   0.02034   0.01429  -0.0135   1.0000   0.0227
  -9.500  -0.9862   0.01975   0.01363  -0.0120   1.0000   0.0240
  -9.250  -0.9666   0.01922   0.01301  -0.0106   1.0000   0.0251
  -9.000  -0.9509   0.01822   0.01191  -0.0087   1.0000   0.0262
  -8.750  -0.9350   0.01733   0.01100  -0.0068   1.0000   0.0277
  -8.500  -0.9155   0.01682   0.01047  -0.0053   1.0000   0.0294
  -8.250  -0.8959   0.01632   0.00991  -0.0038   1.0000   0.0308
  -8.000  -0.8748   0.01599   0.00950  -0.0025   1.0000   0.0323
  -7.750  -0.8605   0.01499   0.00848  -0.0001   1.0000   0.0349
  -7.500  -0.8409   0.01454   0.00802   0.0014   1.0000   0.0371
  -7.250  -0.8210   0.01416   0.00758   0.0029   1.0000   0.0392
  -7.000  -0.8029   0.01360   0.00698   0.0048   1.0000   0.0419
  -6.750  -0.7844   0.01311   0.00649   0.0066   1.0000   0.0455
  -6.500  -0.7644   0.01278   0.00612   0.0081   1.0000   0.0490
  -6.250  -0.7463   0.01228   0.00561   0.0100   1.0000   0.0539
  -6.000  -0.7267   0.01194   0.00527   0.0116   1.0000   0.0600
  -5.750  -0.7080   0.01150   0.00488   0.0133   1.0000   0.0691
  -5.500  -0.6890   0.01110   0.00453   0.0150   1.0000   0.0823
  -5.250  -0.6702   0.01070   0.00424   0.0167   1.0000   0.1032
  -5.000  -0.6509   0.01034   0.00401   0.0183   1.0000   0.1298
  -4.750  -0.6309   0.01008   0.00384   0.0197   1.0000   0.1545
  -4.500  -0.6107   0.00984   0.00370   0.0211   1.0000   0.1766
  -4.250  -0.5762   0.00964   0.00357   0.0195   0.9977   0.2012
  -4.000  -0.5395   0.00940   0.00344   0.0175   0.9946   0.2256
  -3.750  -0.5006   0.00916   0.00329   0.0150   0.9907   0.2512
  -3.500  -0.4618   0.00890   0.00314   0.0126   0.9869   0.2789
  -3.250  -0.4257   0.00863   0.00300   0.0107   0.9831   0.3112
  -3.000  -0.3884   0.00835   0.00286   0.0086   0.9803   0.3472
  -2.750  -0.3547   0.00804   0.00272   0.0073   0.9747   0.3886
  -2.500  -0.3152   0.00766   0.00256   0.0047   0.9712   0.4418
  -2.250  -0.2830   0.00731   0.00242   0.0039   0.9645   0.4941
  -2.000  -0.2453   0.00694   0.00228   0.0018   0.9604   0.5521
  -1.750  -0.2117   0.00663   0.00216   0.0008   0.9534   0.6026
  -1.500  -0.1770   0.00633   0.00206  -0.0004   0.9464   0.6518
  -1.250  -0.1473   0.00610   0.00198  -0.0005   0.9361   0.6958
  -1.000  -0.1161   0.00589   0.00192  -0.0009   0.9254   0.7378
  -0.750  -0.0856   0.00573   0.00188  -0.0010   0.9132   0.7761
  -0.500  -0.0566   0.00562   0.00186  -0.0008   0.8984   0.8088
  -0.250  -0.0287   0.00556   0.00185  -0.0003   0.8811   0.8370
   0.000   0.0000   0.00554   0.00185   0.0000   0.8603   0.8600
   0.250   0.0287   0.00556   0.00185   0.0003   0.8367   0.8810
   0.500   0.0568   0.00562   0.00185   0.0007   0.8077   0.8978
   0.750   0.0856   0.00573   0.00188   0.0010   0.7762   0.9133
   1.000   0.1160   0.00589   0.00192   0.0009   0.7390   0.9262
   1.250   0.1474   0.00610   0.00198   0.0005   0.6961   0.9362
   1.500   0.1769   0.00634   0.00205   0.0005   0.6510   0.9464
   1.750   0.2118   0.00664   0.00217  -0.0008   0.6025   0.9535
   2.000   0.2454   0.00694   0.00228  -0.0019   0.5510   0.9604
   2.250   0.2830   0.00731   0.00242  -0.0039   0.4922   0.9645
   2.500   0.3151   0.00765   0.00257  -0.0047   0.4438   0.9712
   2.750   0.3548   0.00804   0.00272  -0.0073   0.3885   0.9747
   3.000   0.3884   0.00835   0.00286  -0.0085   0.3471   0.9802
   3.250   0.4254   0.00863   0.00300  -0.0106   0.3111   0.9831
   3.500   0.4619   0.00891   0.00314  -0.0126   0.2779   0.9869
   3.750   0.5006   0.00916   0.00329  -0.0150   0.2511   0.9908
   4.000   0.5394   0.00941   0.00344  -0.0174   0.2250   0.9946
   4.250   0.5763   0.00963   0.00357  -0.0195   0.2013   0.9977
   4.500   0.6106   0.00984   0.00370  -0.0211   0.1765   1.0000
   4.750   0.6308   0.01007   0.00384  -0.0197   0.1549   1.0000
   5.000   0.6507   0.01035   0.00401  -0.0182   0.1292   1.0000
   5.250   0.6699   0.01071   0.00424  -0.0166   0.1021   1.0000
   5.500   0.6889   0.01110   0.00453  -0.0150   0.0818   1.0000
   5.750   0.7079   0.01150   0.00488  -0.0133   0.0688   1.0000
   6.000   0.7265   0.01194   0.00528  -0.0115   0.0597   1.0000
   6.250   0.7461   0.01228   0.00562  -0.0099   0.0538   1.0000
   6.500   0.7643   0.01278   0.00613  -0.0081   0.0489   1.0000
   6.750   0.7842   0.01312   0.00651  -0.0065   0.0457   1.0000
   7.000   0.8027   0.01361   0.00700  -0.0047   0.0422   1.0000
   7.250   0.8204   0.01421   0.00764  -0.0028   0.0394   1.0000
   7.500   0.8408   0.01455   0.00802  -0.0014   0.0371   1.0000
   7.750   0.8604   0.01499   0.00849   0.0002   0.0349   1.0000
   8.000   0.8746   0.01600   0.00950   0.0025   0.0322   1.0000
   8.250   0.8957   0.01633   0.00992   0.0038   0.0309   1.0000
   8.500   0.9155   0.01682   0.01046   0.0053   0.0294   1.0000
   8.750   0.9349   0.01734   0.01102   0.0068   0.0278   1.0000
   9.000   0.9519   0.01811   0.01181   0.0085   0.0264   1.0000
   9.250   0.9662   0.01928   0.01306   0.0107   0.0252   1.0000
   9.500   0.9866   0.01970   0.01358   0.0120   0.0240   1.0000
   9.750   1.0053   0.02032   0.01427   0.0134   0.0228   1.0000
  10.000   1.0230   0.02099   0.01499   0.0149   0.0219   1.0000
  10.250   1.0388   0.02186   0.01589   0.0167   0.0209   1.0000
  10.500   1.0472   0.02379   0.01793   0.0193   0.0200   1.0000
  10.750   1.0641   0.02446   0.01874   0.0209   0.0195   1.0000
  11.000   1.0782   0.02546   0.01989   0.0228   0.0189   1.0000
  11.250   1.0915   0.02646   0.02100   0.0246   0.0183   1.0000
  11.500   1.1027   0.02762   0.02228   0.0267   0.0178   1.0000
  11.750   1.1135   0.02863   0.02337   0.0287   0.0172   1.0000
  12.000   1.1215   0.02951   0.02431   0.0312   0.0168   1.0000
  12.250   1.1251   0.03087   0.02575   0.0339   0.0164   1.0000
  12.500   1.1251   0.03270   0.02769   0.0365   0.0160   1.0000
  12.750   1.1160   0.03556   0.03078   0.0390   0.0156   1.0000
  13.000   1.1172   0.03731   0.03270   0.0403   0.0154   1.0000
  13.250   1.1120   0.04003   0.03562   0.0411   0.0153   1.0000
  13.500   1.1079   0.04285   0.03862   0.0411   0.0151   1.0000
  13.750   1.0972   0.04690   0.04287   0.0400   0.0150   1.0000
  14.000   1.0880   0.05120   0.04735   0.0378   0.0149   1.0000
  14.250   1.0744   0.05668   0.05303   0.0344   0.0148   1.0000
  14.500   1.0556   0.06353   0.06008   0.0299   0.0149   1.0000
  14.750   1.0345   0.07131   0.06805   0.0245   0.0149   1.0000
  15.000   1.0046   0.08113   0.07807   0.0178   0.0150   1.0000
  15.250   0.9736   0.09145   0.08854   0.0112   0.0151   1.0000
  15.500   0.9361   0.10368   0.10094   0.0036   0.0152   1.0000
<< Back to WORTMANN FX 76-100 (fx76100-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 76-100 (fx76100-il)