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HOBIE (hobie-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HOBIE (hobie-il)
Reynolds number: 100,000
Max Cl/Cd: 59.81 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobie-il-100000.txt
Download as CSV file: xf-hobie-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HOBIE                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3770   0.11194   0.10662  -0.0253   1.0000   0.0866
  -9.500  -0.3817   0.10995   0.10469  -0.0279   1.0000   0.0897
  -9.250  -0.3991   0.10923   0.10411  -0.0324   1.0000   0.0909
  -9.000  -0.3771   0.10303   0.09788  -0.0293   1.0000   0.0934
  -8.750  -0.3650   0.10005   0.09490  -0.0281   1.0000   0.0980
  -8.500  -0.3720   0.09822   0.09316  -0.0301   1.0000   0.1035
  -8.250  -0.3928   0.09732   0.09243  -0.0328   1.0000   0.1047
  -8.000  -0.3658   0.09192   0.08696  -0.0294   1.0000   0.1093
  -7.750  -0.3639   0.08958   0.08467  -0.0288   1.0000   0.1140
  -7.500  -0.3826   0.08836   0.08361  -0.0298   1.0000   0.1178
  -7.250  -0.3991   0.08556   0.08096  -0.0366   1.0000   0.1198
  -7.000  -0.3776   0.08227   0.07764  -0.0278   1.0000   0.1241
  -6.750  -0.3795   0.08008   0.07552  -0.0281   1.0000   0.1300
  -6.500  -0.3932   0.07682   0.07235  -0.0360   1.0000   0.1346
  -6.250  -0.3834   0.07479   0.07038  -0.0278   1.0000   0.1390
  -6.000  -0.3904   0.07165   0.06718  -0.0389   1.0000   0.1489
  -5.750  -0.3868   0.06970   0.06538  -0.0289   1.0000   0.1522
  -5.500  -0.3842   0.06660   0.06219  -0.0358   1.0000   0.1642
  -5.250  -0.3826   0.06466   0.06037  -0.0293   1.0000   0.1670
  -5.000  -0.3739   0.06152   0.05714  -0.0339   1.0000   0.1795
  -4.750  -0.3703   0.05964   0.05533  -0.0294   1.0000   0.1833
  -4.500  -0.3485   0.05716   0.05253  -0.0376   1.0000   0.2073
  -4.250  -0.3459   0.05423   0.04978  -0.0328   1.0000   0.2102
  -4.000  -0.2662   0.03388   0.02755  -0.0569   1.0000   0.1164
  -3.750  -0.2390   0.03041   0.02355  -0.0585   1.0000   0.1151
  -3.500  -0.2058   0.02734   0.01989  -0.0605   0.9984   0.1130
  -3.250  -0.1585   0.02527   0.01718  -0.0646   0.9917   0.1168
  -3.000  -0.1121   0.02370   0.01504  -0.0682   0.9847   0.1186
  -2.750  -0.0716   0.02246   0.01372  -0.0711   0.9771   0.1240
  -2.500  -0.0272   0.02156   0.01263  -0.0743   0.9709   0.1278
  -2.250   0.0101   0.02089   0.01177  -0.0761   0.9622   0.1321
  -2.000   0.0551   0.02018   0.01114  -0.0795   0.9562   0.1402
  -1.750   0.0902   0.01967   0.01060  -0.0809   0.9461   0.1470
  -1.500   0.1313   0.01911   0.01015  -0.0834   0.9384   0.1578
  -1.250   0.1707   0.01861   0.00984  -0.0856   0.9296   0.1817
  -1.000   0.2079   0.01782   0.00968  -0.0874   0.9207   0.3002
  -0.750   0.2520   0.01718   0.00952  -0.0904   0.9134   0.4573
  -0.500   0.2854   0.01631   0.00947  -0.0908   0.9033   0.6666
  -0.250   0.3481   0.01540   0.00888  -0.0965   0.8977   1.0000
   0.000   0.3855   0.01530   0.00860  -0.0978   0.8853   1.0000
   0.250   0.4237   0.01514   0.00828  -0.0991   0.8731   1.0000
   0.500   0.4614   0.01493   0.00794  -0.1001   0.8607   1.0000
   0.750   0.4975   0.01472   0.00762  -0.1008   0.8483   1.0000
   1.000   0.5317   0.01454   0.00736  -0.1011   0.8357   1.0000
   1.250   0.5607   0.01453   0.00726  -0.1006   0.8212   1.0000
   1.500   0.5890   0.01455   0.00721  -0.1000   0.8065   1.0000
   1.750   0.6168   0.01460   0.00721  -0.0993   0.7915   1.0000
   2.000   0.6442   0.01466   0.00721  -0.0986   0.7761   1.0000
   2.250   0.6713   0.01475   0.00723  -0.0977   0.7603   1.0000
   2.500   0.6980   0.01487   0.00729  -0.0969   0.7446   1.0000
   2.750   0.7244   0.01503   0.00742  -0.0961   0.7290   1.0000
   3.000   0.7499   0.01522   0.00759  -0.0952   0.7125   1.0000
   3.250   0.7755   0.01543   0.00777  -0.0943   0.6965   1.0000
   3.500   0.8012   0.01564   0.00799  -0.0935   0.6809   1.0000
   3.750   0.8266   0.01584   0.00820  -0.0926   0.6650   1.0000
   4.000   0.8514   0.01601   0.00837  -0.0915   0.6474   1.0000
   4.250   0.8762   0.01613   0.00849  -0.0904   0.6290   1.0000
   4.500   0.9011   0.01621   0.00857  -0.0893   0.6100   1.0000
   4.750   0.9260   0.01635   0.00868  -0.0881   0.5912   1.0000
   5.000   0.9496   0.01654   0.00893  -0.0870   0.5708   1.0000
   5.250   0.9736   0.01671   0.00908  -0.0857   0.5490   1.0000
   5.500   0.9962   0.01692   0.00932  -0.0843   0.5247   1.0000
   5.750   1.0188   0.01717   0.00954  -0.0829   0.4999   1.0000
   6.000   1.0396   0.01741   0.00979  -0.0812   0.4696   1.0000
   6.250   1.0593   0.01771   0.01010  -0.0793   0.4354   1.0000
   6.500   1.0767   0.01812   0.01043  -0.0772   0.3904   1.0000
   6.750   1.0895   0.01876   0.01080  -0.0744   0.3055   1.0000
   7.000   1.0914   0.02099   0.01206  -0.0706   0.1805   1.0000
   7.250   1.1005   0.02291   0.01340  -0.0680   0.1164   1.0000
   7.500   1.1108   0.02460   0.01496  -0.0654   0.1007   1.0000
   7.750   1.1214   0.02625   0.01657  -0.0628   0.0911   1.0000
   8.000   1.1326   0.02815   0.01834  -0.0604   0.0846   1.0000
   8.250   1.1512   0.02980   0.02006  -0.0589   0.0788   1.0000
   8.500   1.1730   0.03189   0.02201  -0.0581   0.0730   1.0000
   8.750   1.2037   0.03461   0.02475  -0.0582   0.0696   1.0000
   9.000   1.2273   0.03656   0.02695  -0.0573   0.0661   1.0000
   9.250   1.2510   0.03886   0.02938  -0.0568   0.0625   1.0000
   9.500   1.2762   0.04190   0.03256  -0.0564   0.0607   1.0000
   9.750   1.2984   0.04568   0.03656  -0.0558   0.0596   1.0000
  10.000   1.3139   0.05113   0.04236  -0.0550   0.0585   1.0000
  10.250   1.3179   0.05292   0.04465  -0.0520   0.0576   1.0000
  10.500   1.3212   0.05588   0.04806  -0.0493   0.0572   1.0000
  10.750   1.3246   0.06014   0.05268  -0.0472   0.0575   1.0000
  11.000   1.3338   0.06636   0.05915  -0.0464   0.0587   1.0000
  11.250   1.3301   0.06730   0.06051  -0.0428   0.0597   1.0000
  11.500   1.2929   0.06951   0.06332  -0.0370   0.0615   1.0000
  11.750   1.2570   0.07341   0.06761  -0.0335   0.0631   1.0000
  12.000   1.2265   0.07831   0.07281  -0.0325   0.0645   1.0000
  12.250   1.1975   0.08400   0.07873  -0.0332   0.0657   1.0000
  12.500   1.1689   0.09046   0.08538  -0.0354   0.0667   1.0000
  12.750   1.1404   0.09788   0.09295  -0.0391   0.0678   1.0000
  13.000   1.1210   0.10564   0.10080  -0.0425   0.0694   1.0000
  13.250   0.8272   0.14218   0.13784  -0.0662   0.0931   1.0000
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