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Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 2 (fg2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.17 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg2-il-1000000-n5.txt
Download as CSV file: xf-fg2-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 2                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4453   0.08826   0.08674  -0.0165   1.0000   0.0042
  -8.500  -0.4485   0.08537   0.08388  -0.0169   1.0000   0.0043
  -8.250  -0.4481   0.07913   0.07765  -0.0237   0.9976   0.0042
  -8.000  -0.4269   0.07493   0.07344  -0.0304   0.9953   0.0047
  -7.750  -0.4138   0.06750   0.06597  -0.0395   0.9917   0.0047
  -7.500  -0.3976   0.05896   0.05733  -0.0490   0.9882   0.0052
  -7.250  -0.3964   0.04454   0.04258  -0.0576   0.9813   0.0060
  -7.000  -0.3754   0.03920   0.03704  -0.0602   0.9763   0.0063
  -6.750  -0.3566   0.03733   0.03509  -0.0598   0.9688   0.0066
  -6.250  -0.3563   0.02160   0.01821  -0.0528   0.9383   0.0088
  -6.000  -0.3213   0.02109   0.01767  -0.0546   0.9307   0.0093
  -5.750  -0.2846   0.01797   0.01418  -0.0571   0.9227   0.0106
  -5.500  -0.2316   0.01558   0.01146  -0.0631   0.9133   0.0121
  -5.250  -0.1671   0.01513   0.01085  -0.0717   0.8999   0.0132
  -5.000  -0.1330   0.01211   0.00724  -0.0733   0.8774   0.0162
  -4.750  -0.1027   0.01249   0.00750  -0.0738   0.8420   0.0165
  -4.500  -0.0813   0.01264   0.00746  -0.0723   0.7941   0.0169
  -4.250  -0.0633   0.01270   0.00727  -0.0701   0.7363   0.0173
  -4.000  -0.0433   0.01278   0.00713  -0.0683   0.6908   0.0180
  -3.750  -0.0219   0.01255   0.00670  -0.0669   0.6563   0.0188
  -3.500   0.0006   0.01217   0.00612  -0.0657   0.6299   0.0197
  -3.250   0.0239   0.01197   0.00575  -0.0646   0.6060   0.0205
  -3.000   0.0479   0.01168   0.00533  -0.0637   0.5885   0.0210
  -2.750   0.0722   0.01148   0.00501  -0.0629   0.5726   0.0213
  -2.500   0.0967   0.01120   0.00462  -0.0621   0.5596   0.0215
  -2.250   0.1212   0.01092   0.00425  -0.0613   0.5471   0.0216
  -2.000   0.1463   0.01087   0.00413  -0.0607   0.5355   0.0218
  -1.750   0.1685   0.00992   0.00312  -0.0595   0.5253   0.0226
  -1.500   0.1920   0.00962   0.00277  -0.0585   0.5146   0.0231
  -1.250   0.2160   0.00944   0.00255  -0.0577   0.5035   0.0238
  -1.000   0.2401   0.00928   0.00236  -0.0568   0.4914   0.0242
  -0.750   0.2638   0.00921   0.00221  -0.0559   0.4721   0.0249
  -0.500   0.2880   0.00911   0.00205  -0.0551   0.4597   0.0253
  -0.250   0.3118   0.00907   0.00193  -0.0542   0.4383   0.0258
   0.000   0.3358   0.00901   0.00180  -0.0533   0.4216   0.0261
   0.250   0.3593   0.00901   0.00169  -0.0524   0.3999   0.0261
   0.500   0.3832   0.00902   0.00163  -0.0515   0.3796   0.0264
   0.750   0.4075   0.00902   0.00157  -0.0508   0.3663   0.0268
   1.000   0.4319   0.00903   0.00153  -0.0500   0.3544   0.0272
   1.250   0.4564   0.00904   0.00149  -0.0493   0.3436   0.0273
   1.500   0.4811   0.00905   0.00146  -0.0486   0.3338   0.0273
   1.750   0.5058   0.00908   0.00145  -0.0480   0.3257   0.0273
   2.000   0.5306   0.00910   0.00145  -0.0473   0.3173   0.0276
   2.250   0.5555   0.00914   0.00147  -0.0467   0.3107   0.0276
   2.500   0.5807   0.00917   0.00149  -0.0462   0.3052   0.0279
   2.750   0.6056   0.00924   0.00153  -0.0456   0.2987   0.0284
   3.000   0.6309   0.00928   0.00157  -0.0450   0.2942   0.0291
   3.250   0.6561   0.00932   0.00162  -0.0445   0.2893   0.0331
   3.750   0.8571   0.00815   0.00247  -0.0795   0.2536   1.0000
   4.000   0.8796   0.00838   0.00259  -0.0785   0.2281   1.0000
   4.250   0.8972   0.00900   0.00288  -0.0767   0.1654   1.0000
   4.500   0.9178   0.00939   0.00314  -0.0753   0.1390   1.0000
   4.750   0.9394   0.00970   0.00337  -0.0741   0.1210   1.0000
   5.000   0.9614   0.00998   0.00358  -0.0731   0.1080   1.0000
   5.250   0.9836   0.01025   0.00380  -0.0720   0.0959   1.0000
   5.750   1.0176   0.01163   0.00478  -0.0681   0.0151   1.0000
   6.000   1.0393   0.01192   0.00509  -0.0669   0.0126   1.0000
   6.250   1.0605   0.01227   0.00547  -0.0657   0.0097   1.0000
   6.500   1.0824   0.01253   0.00577  -0.0646   0.0090   1.0000
   6.750   1.1037   0.01283   0.00611  -0.0635   0.0081   1.0000
   7.000   1.1244   0.01318   0.00648  -0.0622   0.0073   1.0000
   7.250   1.1436   0.01365   0.00699  -0.0606   0.0063   1.0000
   7.500   1.1641   0.01399   0.00738  -0.0593   0.0061   1.0000
   7.750   1.1841   0.01436   0.00780  -0.0580   0.0057   1.0000
   8.000   1.2038   0.01474   0.00822  -0.0566   0.0052   1.0000
   8.250   1.2231   0.01514   0.00864  -0.0551   0.0048   1.0000
   8.500   1.2402   0.01569   0.00923  -0.0533   0.0042   1.0000
   8.750   1.2573   0.01623   0.00984  -0.0515   0.0041   1.0000
   9.000   1.2740   0.01678   0.01046  -0.0496   0.0040   1.0000
   9.250   1.2915   0.01723   0.01098  -0.0479   0.0037   1.0000
   9.500   1.3065   0.01785   0.01167  -0.0458   0.0036   1.0000
   9.750   1.3216   0.01844   0.01233  -0.0437   0.0034   1.0000
  10.000   1.3340   0.01917   0.01315  -0.0411   0.0034   1.0000
  10.250   1.3474   0.01979   0.01383  -0.0388   0.0032   1.0000
  10.500   1.3600   0.02033   0.01442  -0.0364   0.0030   1.0000
  10.750   1.3664   0.02100   0.01516  -0.0327   0.0030   1.0000
  11.000   1.3735   0.02167   0.01587  -0.0294   0.0028   1.0000
  11.250   1.3784   0.02249   0.01681  -0.0258   0.0028   1.0000
  11.500   1.3782   0.02367   0.01809  -0.0217   0.0026   1.0000
  11.750   1.3799   0.02481   0.01934  -0.0182   0.0025   1.0000
  12.000   1.3819   0.02603   0.02065  -0.0150   0.0026   1.0000
  12.250   1.3887   0.02703   0.02174  -0.0127   0.0025   1.0000
  12.500   1.3878   0.02862   0.02346  -0.0099   0.0024   1.0000
  12.750   1.3889   0.03022   0.02516  -0.0077   0.0024   1.0000
  13.000   1.3951   0.03156   0.02659  -0.0063   0.0023   1.0000
  13.250   1.3843   0.03452   0.02970  -0.0043   0.0023   1.0000
  13.500   1.3819   0.03705   0.03236  -0.0034   0.0022   1.0000
  13.750   1.3748   0.04039   0.03583  -0.0031   0.0022   1.0000
  14.000   1.3824   0.04227   0.03780  -0.0033   0.0021   1.0000
  14.250   1.3707   0.04672   0.04239  -0.0041   0.0021   1.0000
  14.500   1.3591   0.05142   0.04724  -0.0052   0.0021   1.0000
  14.750   1.3510   0.05576   0.05170  -0.0065   0.0021   1.0000
  15.000   1.3340   0.06140   0.05750  -0.0082   0.0021   1.0000
  15.250   1.3326   0.06498   0.06116  -0.0094   0.0020   1.0000
  15.500   1.3326   0.06841   0.06466  -0.0107   0.0019   1.0000
  15.750   1.3044   0.07600   0.07243  -0.0132   0.0020   1.0000
  16.000   1.2846   0.08260   0.07917  -0.0155   0.0020   1.0000
  16.250   1.2785   0.08730   0.08394  -0.0174   0.0019   1.0000
  16.500   1.2694   0.09252   0.08926  -0.0195   0.0019   1.0000
  16.750   1.2520   0.09918   0.09604  -0.0221   0.0019   1.0000
  17.000   1.2409   0.10494   0.10189  -0.0245   0.0019   1.0000
  17.250   1.2267   0.11126   0.10831  -0.0270   0.0019   1.0000
  17.500   1.2138   0.11749   0.11465  -0.0297   0.0019   1.0000
  17.750   1.1979   0.12437   0.12164  -0.0326   0.0019   1.0000
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