Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HOBIE (hobie-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HOBIE (hobie-il)
Reynolds number: 50,000
Max Cl/Cd: 41.78 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hobie-il-50000-n5.txt
Download as CSV file: xf-hobie-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3822   0.09510   0.08828  -0.0371   1.0000   0.0653
  -8.000  -0.3782   0.09176   0.08498  -0.0361   1.0000   0.0645
  -7.750  -0.3803   0.08859   0.08191  -0.0363   1.0000   0.0642
  -7.500  -0.3823   0.08514   0.07856  -0.0377   1.0000   0.0643
  -7.250  -0.3839   0.08147   0.07498  -0.0396   1.0000   0.0644
  -7.000  -0.3844   0.07751   0.07109  -0.0418   1.0000   0.0646
  -6.750  -0.3836   0.07328   0.06690  -0.0443   1.0000   0.0647
  -6.500  -0.3811   0.06872   0.06234  -0.0469   1.0000   0.0647
  -6.250  -0.3767   0.06374   0.05730  -0.0498   1.0000   0.0646
  -6.000  -0.3691   0.05733   0.05066  -0.0549   1.0000   0.0653
  -5.750  -0.3618   0.05561   0.04904  -0.0532   1.0000   0.0683
  -5.500  -0.3506   0.05249   0.04581  -0.0541   1.0000   0.0710
  -5.250  -0.3343   0.04760   0.04059  -0.0573   1.0000   0.0729
  -5.000  -0.3129   0.04246   0.03487  -0.0612   1.0000   0.0774
  -4.750  -0.2867   0.03732   0.02880  -0.0648   1.0000   0.0810
  -4.500  -0.2700   0.03593   0.02746  -0.0642   1.0000   0.0860
  -4.250  -0.2467   0.03351   0.02458  -0.0650   1.0000   0.0909
  -4.000  -0.2163   0.03097   0.02130  -0.0669   0.9980   0.0971
  -3.750  -0.1796   0.02944   0.01953  -0.0695   0.9915   0.1024
  -3.500  -0.1410   0.02793   0.01750  -0.0721   0.9851   0.1079
  -3.250  -0.1042   0.02689   0.01623  -0.0744   0.9779   0.1148
  -3.000  -0.0678   0.02590   0.01495  -0.0763   0.9703   0.1185
  -2.750  -0.0312   0.02507   0.01382  -0.0781   0.9624   0.1225
  -2.500   0.0063   0.02438   0.01296  -0.0800   0.9542   0.1275
  -2.250   0.0462   0.02382   0.01223  -0.0824   0.9452   0.1351
  -2.000   0.0839   0.02330   0.01163  -0.0843   0.9345   0.1456
  -1.750   0.1213   0.02284   0.01120  -0.0863   0.9237   0.1699
  -1.500   0.1596   0.02234   0.01090  -0.0883   0.9138   0.2197
  -1.250   0.1984   0.02181   0.01062  -0.0905   0.9052   0.2999
  -1.000   0.2306   0.02154   0.01050  -0.0914   0.8948   0.3806
  -0.500   0.2927   0.02026   0.01035  -0.0920   0.8769   0.6521
  -0.250   0.3306   0.01969   0.01005  -0.0933   0.8668   1.0000
   0.000   0.3683   0.01974   0.00984  -0.0949   0.8580   1.0000
   0.250   0.3982   0.01991   0.00980  -0.0952   0.8460   1.0000
   0.500   0.4293   0.02005   0.00978  -0.0956   0.8346   1.0000
   0.750   0.4631   0.02013   0.00971  -0.0964   0.8246   1.0000
   1.000   0.4944   0.02025   0.00972  -0.0968   0.8131   1.0000
   1.250   0.5233   0.02042   0.00981  -0.0967   0.8004   1.0000
   1.500   0.5531   0.02055   0.00987  -0.0967   0.7878   1.0000
   1.750   0.5835   0.02065   0.00991  -0.0967   0.7750   1.0000
   2.000   0.6137   0.02072   0.00992  -0.0966   0.7615   1.0000
   2.250   0.6433   0.02079   0.00995  -0.0963   0.7476   1.0000
   2.500   0.6718   0.02088   0.01003  -0.0959   0.7331   1.0000
   2.750   0.6989   0.02103   0.01017  -0.0952   0.7179   1.0000
   3.000   0.7253   0.02123   0.01039  -0.0945   0.7027   1.0000
   3.250   0.7512   0.02146   0.01064  -0.0938   0.6876   1.0000
   3.500   0.7768   0.02171   0.01094  -0.0931   0.6726   1.0000
   3.750   0.8023   0.02197   0.01127  -0.0923   0.6575   1.0000
   4.000   0.8275   0.02224   0.01161  -0.0915   0.6425   1.0000
   4.250   0.8527   0.02254   0.01199  -0.0907   0.6279   1.0000
   4.500   0.8777   0.02283   0.01240  -0.0899   0.6129   1.0000
   4.750   0.9026   0.02312   0.01278  -0.0890   0.5973   1.0000
   5.000   0.9274   0.02344   0.01322  -0.0881   0.5822   1.0000
   5.250   0.9522   0.02380   0.01373  -0.0873   0.5674   1.0000
   5.500   0.9768   0.02417   0.01424  -0.0864   0.5521   1.0000
   5.750   1.0007   0.02449   0.01468  -0.0852   0.5342   1.0000
   6.000   1.0245   0.02477   0.01509  -0.0839   0.5148   1.0000
   6.250   1.0450   0.02519   0.01566  -0.0823   0.4918   1.0000
   6.500   1.0661   0.02552   0.01607  -0.0807   0.4676   1.0000
   6.750   1.0841   0.02596   0.01660  -0.0786   0.4391   1.0000
   7.000   1.1015   0.02649   0.01723  -0.0766   0.4098   1.0000
   7.250   1.1149   0.02711   0.01794  -0.0741   0.3719   1.0000
   7.500   1.1218   0.02792   0.01861  -0.0708   0.3112   1.0000
   7.750   1.1236   0.02944   0.01957  -0.0674   0.2326   1.0000
   8.000   1.1246   0.03161   0.02136  -0.0643   0.1645   1.0000
   8.250   1.1220   0.03416   0.02333  -0.0613   0.1097   1.0000
   8.500   1.1197   0.03662   0.02557  -0.0583   0.0928   1.0000
   8.750   1.1181   0.03912   0.02802  -0.0556   0.0825   1.0000
   9.000   1.1197   0.04145   0.03045  -0.0533   0.0747   1.0000
   9.250   1.1201   0.04399   0.03301  -0.0512   0.0689   1.0000
   9.500   1.1260   0.04631   0.03549  -0.0493   0.0637   1.0000
   9.750   1.1342   0.04856   0.03786  -0.0477   0.0586   1.0000
  10.000   1.1509   0.05081   0.04010  -0.0461   0.0541   1.0000
  10.250   1.1704   0.05285   0.04253  -0.0447   0.0499   1.0000
  10.500   1.1879   0.05520   0.04511  -0.0436   0.0462   1.0000
  10.750   1.2099   0.05797   0.04799  -0.0428   0.0435   1.0000
  11.000   1.2262   0.06140   0.05162  -0.0420   0.0414   1.0000
  11.250   1.2265   0.06453   0.05518  -0.0405   0.0403   1.0000
  11.500   1.2238   0.06805   0.05908  -0.0393   0.0393   1.0000
  11.750   1.2181   0.07195   0.06333  -0.0385   0.0386   1.0000
  12.000   1.2092   0.07622   0.06793  -0.0381   0.0383   1.0000
  12.250   1.1969   0.08093   0.07294  -0.0384   0.0381   1.0000
  12.500   1.1819   0.08609   0.07838  -0.0394   0.0380   1.0000
  12.750   1.1646   0.09182   0.08436  -0.0413   0.0380   1.0000
  13.000   1.1455   0.09820   0.09097  -0.0441   0.0382   1.0000
  13.250   1.1252   0.10530   0.09829  -0.0478   0.0384   1.0000
  13.500   1.1041   0.11320   0.10636  -0.0525   0.0387   1.0000
<< Back to HOBIE (hobie-il)

Polar data table (+)

Polar graphs


<< Back to HOBIE (hobie-il)