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

I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 962 (isa962-il)
Reynolds number: 100,000
Max Cl/Cd: 57.48 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa962-il-100000.txt
Download as CSV file: xf-isa962-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 962                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3216   0.09936   0.09456  -0.0281   1.0000   0.0950
  -8.500  -0.3469   0.09965   0.09499  -0.0274   1.0000   0.0956
  -8.250  -0.3678   0.09969   0.09510  -0.0299   1.0000   0.0961
  -8.000  -0.3720   0.09636   0.09185  -0.0286   1.0000   0.0967
  -7.750  -0.3660   0.09237   0.08792  -0.0226   1.0000   0.0977
  -7.500  -0.3652   0.08992   0.08552  -0.0191   1.0000   0.0989
  -7.250  -0.3677   0.08796   0.08362  -0.0169   1.0000   0.1003
  -7.000  -0.3710   0.08610   0.08180  -0.0156   1.0000   0.1021
  -6.750  -0.3736   0.08417   0.07991  -0.0153   1.0000   0.1042
  -6.500  -0.3736   0.08213   0.07789  -0.0171   1.0000   0.1074
  -6.250  -0.3492   0.07786   0.07347  -0.0295   0.9966   0.1116
  -6.000  -0.3272   0.07408   0.06974  -0.0290   0.9921   0.1139
  -5.750  -0.2960   0.07074   0.06636  -0.0331   0.9858   0.1196
  -5.500  -0.2528   0.06599   0.06141  -0.0444   0.9782   0.1283
  -5.250  -0.2231   0.06290   0.05834  -0.0467   0.9725   0.1332
  -5.000  -0.1802   0.05899   0.05417  -0.0561   0.9645   0.1442
  -4.750  -0.1490   0.05605   0.05126  -0.0582   0.9590   0.1495
  -4.500  -0.1115   0.05289   0.04791  -0.0643   0.9510   0.1618
  -4.250  -0.0688   0.05018   0.04499  -0.0702   0.9451   0.1772
  -4.000  -0.0419   0.04777   0.04264  -0.0710   0.9377   0.1844
  -3.750   0.0025   0.04541   0.04006  -0.0767   0.9306   0.2114
  -3.500   0.0363   0.04304   0.03768  -0.0789   0.9230   0.2301
  -3.250   0.0744   0.04076   0.03539  -0.0816   0.9155   0.2517
  -3.000   0.1649   0.03246   0.02537  -0.0939   0.9129   0.1207
  -2.750   0.2038   0.02966   0.02195  -0.0954   0.9038   0.1045
  -2.500   0.2548   0.02760   0.01948  -0.0991   0.8987   0.1035
  -2.250   0.2950   0.02613   0.01770  -0.1008   0.8906   0.1030
  -2.000   0.3372   0.02471   0.01602  -0.1025   0.8830   0.1030
  -1.750   0.3726   0.02374   0.01490  -0.1032   0.8740   0.1049
  -1.500   0.4093   0.02290   0.01392  -0.1040   0.8661   0.1090
  -1.250   0.4389   0.02218   0.01329  -0.1039   0.8566   0.1166
  -1.000   0.4735   0.02139   0.01250  -0.1042   0.8487   0.1269
  -0.750   0.5000   0.02079   0.01205  -0.1035   0.8380   0.1442
  -0.500   0.5431   0.01761   0.01122  -0.1053   0.8321   1.0000
  -0.250   0.5688   0.01773   0.01108  -0.1043   0.8203   1.0000
   0.000   0.6001   0.01757   0.01070  -0.1039   0.8115   1.0000
   0.250   0.6270   0.01747   0.01046  -0.1029   0.7991   1.0000
   0.500   0.6530   0.01737   0.01023  -0.1017   0.7854   1.0000
   0.750   0.6800   0.01719   0.00993  -0.1006   0.7719   1.0000
   1.000   0.7075   0.01699   0.00961  -0.0995   0.7585   1.0000
   1.250   0.7352   0.01676   0.00927  -0.0985   0.7443   1.0000
   1.500   0.7623   0.01659   0.00898  -0.0973   0.7286   1.0000
   1.750   0.7884   0.01648   0.00878  -0.0961   0.7112   1.0000
   2.000   0.8143   0.01645   0.00865  -0.0950   0.6929   1.0000
   2.250   0.8399   0.01644   0.00854  -0.0939   0.6730   1.0000
   2.500   0.8658   0.01643   0.00841  -0.0927   0.6519   1.0000
   2.750   0.8910   0.01649   0.00834  -0.0916   0.6296   1.0000
   3.000   0.9151   0.01663   0.00840  -0.0904   0.6049   1.0000
   3.250   0.9403   0.01679   0.00839  -0.0894   0.5820   1.0000
   3.500   0.9636   0.01705   0.00859  -0.0883   0.5563   1.0000
   3.750   0.9878   0.01731   0.00869  -0.0872   0.5332   1.0000
   4.000   1.0108   0.01764   0.00896  -0.0862   0.5081   1.0000
   4.250   1.0340   0.01799   0.00916  -0.0851   0.4849   1.0000
   4.500   1.0563   0.01840   0.00947  -0.0840   0.4603   1.0000
   4.750   1.0783   0.01886   0.00978  -0.0828   0.4363   1.0000
   5.000   1.0993   0.01941   0.01022  -0.0816   0.4104   1.0000
   5.250   1.1197   0.02009   0.01067  -0.0803   0.3845   1.0000
   5.500   1.1394   0.02090   0.01132  -0.0790   0.3573   1.0000
   5.750   1.1594   0.02186   0.01210  -0.0778   0.3321   1.0000
   6.000   1.1797   0.02281   0.01291  -0.0766   0.3101   1.0000
   6.250   1.2006   0.02372   0.01371  -0.0757   0.2924   1.0000
   6.500   1.2217   0.02456   0.01452  -0.0747   0.2774   1.0000
   6.750   1.2430   0.02538   0.01533  -0.0738   0.2648   1.0000
   7.000   1.2651   0.02621   0.01604  -0.0731   0.2543   1.0000
   7.250   1.2855   0.02697   0.01688  -0.0721   0.2437   1.0000
   7.500   1.3066   0.02784   0.01778  -0.0712   0.2346   1.0000
   7.750   1.3285   0.02867   0.01857  -0.0705   0.2264   1.0000
   8.000   1.3491   0.02969   0.01971  -0.0696   0.2187   1.0000
   8.250   1.3715   0.03061   0.02056  -0.0690   0.2116   1.0000
   8.500   1.3914   0.03178   0.02189  -0.0681   0.2049   1.0000
   8.750   1.4128   0.03284   0.02296  -0.0675   0.1986   1.0000
   9.000   1.4371   0.03426   0.02436  -0.0673   0.1935   1.0000
   9.250   1.4542   0.03563   0.02601  -0.0661   0.1885   1.0000
   9.500   1.4761   0.03692   0.02734  -0.0656   0.1836   1.0000
   9.750   1.5003   0.03870   0.02910  -0.0656   0.1793   1.0000
  10.000   1.5122   0.04033   0.03110  -0.0638   0.1754   1.0000
  10.250   1.5273   0.04193   0.03292  -0.0625   0.1715   1.0000
  10.500   1.5496   0.04341   0.03438  -0.0623   0.1672   1.0000
  10.750   1.5622   0.04551   0.03669  -0.0609   0.1635   1.0000
  11.000   1.5650   0.04728   0.03882  -0.0581   0.1598   1.0000
  11.250   1.5761   0.04856   0.04023  -0.0565   0.1552   1.0000
  11.500   1.6028   0.05027   0.04176  -0.0573   0.1499   1.0000
  11.750   1.5933   0.05217   0.04412  -0.0532   0.1476   1.0000
  12.000   1.5862   0.05421   0.04648  -0.0496   0.1448   1.0000
  12.250   1.5855   0.05589   0.04834  -0.0468   0.1417   1.0000
  12.500   1.5999   0.05699   0.04944  -0.0458   0.1379   1.0000
  12.750   1.6071   0.05913   0.05165  -0.0445   0.1346   1.0000
  13.000   1.5818   0.06197   0.05484  -0.0400   0.1335   1.0000
  13.250   1.5550   0.06554   0.05873  -0.0367   0.1324   1.0000
  13.500   1.5250   0.06997   0.06347  -0.0344   0.1315   1.0000
  13.750   1.4881   0.07581   0.06962  -0.0332   0.1313   1.0000
  14.000   1.4386   0.08421   0.07831  -0.0339   0.1322   1.0000
  14.250   1.3781   0.09575   0.09010  -0.0371   0.1341   1.0000
  14.500   1.4532   0.08675   0.08094  -0.0333   0.1236   1.0000
  14.750   1.4241   0.09354   0.08789  -0.0350   0.1227   1.0000
  15.000   1.3952   0.10105   0.09554  -0.0373   0.1218   1.0000
<< Back to I.S.A. 962 (isa962-il)

Polar data table (+)

Polar graphs


<< Back to I.S.A. 962 (isa962-il)