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

GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 503 AIRFOIL (goe503-il)
Reynolds number: 500,000
Max Cl/Cd: 91.38 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe503-il-500000-n5.txt
Download as CSV file: xf-goe503-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 503 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.2740   0.09815   0.09545  -0.0953   0.9753   0.0101
 -14.000  -0.2927   0.09030   0.08751  -0.0998   0.9711   0.0102
 -13.750  -0.3017   0.08429   0.08144  -0.1038   0.9662   0.0102
 -13.500  -0.3107   0.07772   0.07479  -0.1089   0.9629   0.0103
 -13.250  -0.3185   0.07267   0.06969  -0.1122   0.9559   0.0102
 -13.000  -0.3310   0.06556   0.06248  -0.1185   0.9506   0.0104
 -12.750  -0.3465   0.05859   0.05543  -0.1252   0.9421   0.0104
 -12.500  -0.3808   0.04676   0.04345  -0.1412   0.9292   0.0102
 -12.250  -0.4271   0.03536   0.03166  -0.1512   0.9063   0.0101
 -12.000  -0.4315   0.02969   0.02566  -0.1535   0.8903   0.0101
 -11.750  -0.4194   0.02624   0.02192  -0.1547   0.8750   0.0102
 -11.500  -0.4053   0.02450   0.01993  -0.1542   0.8587   0.0104
 -11.250  -0.3927   0.02314   0.01835  -0.1529   0.8411   0.0105
 -11.000  -0.3827   0.02184   0.01683  -0.1508   0.8230   0.0107
 -10.750  -0.3712   0.02077   0.01556  -0.1487   0.8054   0.0110
 -10.500  -0.3576   0.01991   0.01451  -0.1467   0.7899   0.0112
 -10.250  -0.3429   0.01914   0.01356  -0.1447   0.7765   0.0115
 -10.000  -0.3265   0.01849   0.01276  -0.1429   0.7646   0.0118
  -9.750  -0.3091   0.01790   0.01201  -0.1412   0.7542   0.0122
  -9.500  -0.2909   0.01737   0.01133  -0.1396   0.7449   0.0127
  -9.250  -0.2715   0.01687   0.01068  -0.1382   0.7366   0.0132
  -9.000  -0.2520   0.01639   0.01006  -0.1368   0.7292   0.0137
  -8.750  -0.2327   0.01579   0.00934  -0.1353   0.7224   0.0144
  -8.500  -0.2122   0.01531   0.00876  -0.1340   0.7155   0.0152
  -8.250  -0.1908   0.01493   0.00824  -0.1328   0.7091   0.0160
  -8.000  -0.1687   0.01455   0.00776  -0.1317   0.7027   0.0168
  -7.750  -0.1472   0.01411   0.00723  -0.1305   0.6968   0.0185
  -7.500  -0.1247   0.01376   0.00680  -0.1295   0.6915   0.0204
  -7.250  -0.1024   0.01335   0.00638  -0.1284   0.6855   0.0250
  -7.000  -0.0797   0.01305   0.00608  -0.1274   0.6795   0.0343
  -6.750  -0.0558   0.01286   0.00586  -0.1266   0.6736   0.0403
  -6.500  -0.0318   0.01269   0.00564  -0.1258   0.6676   0.0439
  -6.250  -0.0080   0.01255   0.00544  -0.1250   0.6620   0.0473
  -6.000   0.0165   0.01242   0.00525  -0.1242   0.6562   0.0498
  -5.750   0.0401   0.01225   0.00504  -0.1233   0.6497   0.0531
  -5.500   0.0634   0.01212   0.00485  -0.1223   0.6436   0.0561
  -5.250   0.0875   0.01199   0.00467  -0.1215   0.6369   0.0585
  -5.000   0.1110   0.01189   0.00450  -0.1205   0.6305   0.0609
  -4.750   0.1344   0.01172   0.00431  -0.1196   0.6244   0.0643
  -4.500   0.1576   0.01161   0.00416  -0.1186   0.6171   0.0680
  -4.000   0.2040   0.01139   0.00389  -0.1166   0.6037   0.0767
  -3.750   0.2263   0.01132   0.00377  -0.1154   0.5970   0.0811
  -3.500   0.2496   0.01123   0.00366  -0.1144   0.5903   0.0865
  -3.250   0.2721   0.01117   0.00356  -0.1133   0.5834   0.0928
  -3.000   0.2948   0.01113   0.00347  -0.1122   0.5774   0.0981
  -2.750   0.3175   0.01106   0.00339  -0.1111   0.5708   0.1046
  -2.250   0.3619   0.01099   0.00327  -0.1087   0.5586   0.1171
  -2.000   0.3837   0.01097   0.00322  -0.1074   0.5527   0.1237
  -1.750   0.4046   0.01096   0.00317  -0.1060   0.5474   0.1295
  -1.500   0.4263   0.01092   0.00314  -0.1047   0.5419   0.1370
  -1.250   0.4471   0.01092   0.00311  -0.1032   0.5365   0.1445
  -1.000   0.4676   0.01093   0.00311  -0.1017   0.5319   0.1536
  -0.750   0.4897   0.01091   0.00311  -0.1005   0.5269   0.1642
  -0.500   0.5112   0.01093   0.00312  -0.0992   0.5220   0.1742
  -0.250   0.5318   0.01097   0.00315  -0.0977   0.5174   0.1841
   0.000   0.5538   0.01100   0.00317  -0.0966   0.5132   0.1922
   0.250   0.5759   0.01102   0.00321  -0.0954   0.5090   0.2010
   0.500   0.5972   0.01108   0.00324  -0.0941   0.5043   0.2085
   0.750   0.6178   0.01115   0.00331  -0.0927   0.5001   0.2169
   1.000   0.6406   0.01120   0.00335  -0.0917   0.4964   0.2232
   1.250   0.6624   0.01124   0.00342  -0.0906   0.4924   0.2301
   1.500   0.6835   0.01131   0.00349  -0.0893   0.4881   0.2368
   1.750   0.7035   0.01142   0.00357  -0.0878   0.4837   0.2436
   2.000   0.7260   0.01147   0.00365  -0.0868   0.4802   0.2523
   2.250   0.7477   0.01153   0.00373  -0.0857   0.4761   0.2609
   2.500   0.7679   0.01162   0.00384  -0.0843   0.4717   0.2725
   2.750   0.7875   0.01173   0.00396  -0.0828   0.4677   0.2865
   3.000   0.8091   0.01178   0.00407  -0.0817   0.4643   0.3068
   3.250   0.8297   0.01182   0.00421  -0.0804   0.4602   0.3380
   3.500   0.8483   0.01187   0.00435  -0.0788   0.4559   0.3789
   4.250   1.0301   0.01150   0.00538  -0.1016   0.4401   0.9862
   4.500   1.0597   0.01178   0.00561  -0.1024   0.4354   0.9956
   4.750   1.0975   0.01201   0.00584  -0.1050   0.4295   1.0000
   5.000   1.1111   0.01219   0.00599  -0.1024   0.4238   1.0000
   5.250   1.1245   0.01240   0.00617  -0.0998   0.4185   1.0000
   5.500   1.1404   0.01258   0.00636  -0.0977   0.4123   1.0000
   5.750   1.1541   0.01283   0.00658  -0.0953   0.4062   1.0000
   6.000   1.1695   0.01307   0.00680  -0.0932   0.4001   1.0000
   6.250   1.1842   0.01335   0.00706  -0.0910   0.3929   1.0000
   6.500   1.1988   0.01366   0.00735  -0.0889   0.3876   1.0000
   6.750   1.2161   0.01391   0.00761  -0.0873   0.3827   1.0000
   7.000   1.2320   0.01422   0.00792  -0.0855   0.3773   1.0000
   7.250   1.2466   0.01460   0.00828  -0.0835   0.3725   1.0000
   7.500   1.2640   0.01490   0.00861  -0.0820   0.3676   1.0000
   7.750   1.2794   0.01529   0.00899  -0.0803   0.3620   1.0000
   8.000   1.2934   0.01574   0.00944  -0.0784   0.3568   1.0000
   8.250   1.3098   0.01613   0.00985  -0.0769   0.3507   1.0000
   8.500   1.3230   0.01666   0.01038  -0.0750   0.3446   1.0000
   8.750   1.3374   0.01718   0.01090  -0.0733   0.3381   1.0000
   9.000   1.3493   0.01781   0.01152  -0.0714   0.3300   1.0000
   9.250   1.3605   0.01852   0.01221  -0.0694   0.3202   1.0000
   9.500   1.3701   0.01933   0.01301  -0.0673   0.3121   1.0000
   9.750   1.3827   0.02004   0.01373  -0.0657   0.3041   1.0000
  10.000   1.3906   0.02102   0.01469  -0.0636   0.2945   1.0000
  10.250   1.3985   0.02206   0.01570  -0.0616   0.2834   1.0000
  10.500   1.4086   0.02302   0.01668  -0.0599   0.2758   1.0000
  10.750   1.4127   0.02439   0.01801  -0.0578   0.2631   1.0000
  11.000   1.4209   0.02557   0.01919  -0.0562   0.2546   1.0000
  11.250   1.4245   0.02710   0.02070  -0.0543   0.2425   1.0000
  11.500   1.4289   0.02864   0.02224  -0.0526   0.2328   1.0000
  11.750   1.4284   0.03061   0.02417  -0.0506   0.2186   1.0000
  12.000   1.4261   0.03279   0.02630  -0.0486   0.2043   1.0000
  12.250   1.4219   0.03522   0.02867  -0.0467   0.1895   1.0000
  12.500   1.4187   0.03764   0.03106  -0.0451   0.1779   1.0000
  13.000   1.4102   0.04287   0.03625  -0.0420   0.1549   1.0000
  13.250   1.4057   0.04564   0.03901  -0.0407   0.1432   1.0000
  13.500   1.3906   0.04950   0.04278  -0.0391   0.1236   1.0000
  13.750   1.3712   0.05392   0.04709  -0.0376   0.0977   1.0000
  14.000   1.3416   0.05963   0.05267  -0.0361   0.0664   1.0000
  14.250   1.3198   0.06469   0.05768  -0.0350   0.0455   1.0000
  14.500   1.2934   0.07052   0.06343  -0.0343   0.0193   1.0000
  14.750   1.2898   0.07382   0.06678  -0.0340   0.0163   1.0000
  15.000   1.2892   0.07680   0.06984  -0.0338   0.0150   1.0000
  15.250   1.2871   0.08000   0.07312  -0.0337   0.0138   1.0000
  15.500   1.2855   0.08317   0.07636  -0.0337   0.0130   1.0000
  15.750   1.2842   0.08636   0.07963  -0.0338   0.0123   1.0000
  16.000   1.2841   0.08940   0.08276  -0.0339   0.0120   1.0000
  16.250   1.2828   0.09262   0.08606  -0.0341   0.0114   1.0000
  16.500   1.2807   0.09597   0.08949  -0.0343   0.0109   1.0000
  16.750   1.2775   0.09950   0.09310  -0.0346   0.0104   1.0000
  17.000   1.2730   0.10327   0.09696  -0.0351   0.0100   1.0000
<< Back to GOE 503 AIRFOIL (goe503-il)

Polar data table (+)

Polar graphs


<< Back to GOE 503 AIRFOIL (goe503-il)