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WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 74-080 (fx74080-il)
Reynolds number: 200,000
Max Cl/Cd: 86.97 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74080-il-200000-n5.txt
Download as CSV file: xf-fx74080-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 74-080                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3394   0.13062   0.12709  -0.0432   1.0000   0.0094
 -11.000  -0.3354   0.12753   0.12397  -0.0435   1.0000   0.0097
 -10.750  -0.3304   0.12431   0.12080  -0.0441   0.9930   0.0099
 -10.500  -0.3185   0.12041   0.11690  -0.0471   0.9816   0.0103
 -10.250  -0.3057   0.11651   0.11298  -0.0506   0.9727   0.0104
  -9.750  -0.2779   0.10856   0.10501  -0.0581   0.9592   0.0114
  -9.500  -0.2621   0.10456   0.10099  -0.0625   0.9542   0.0114
  -9.250  -0.2456   0.10046   0.09686  -0.0672   0.9492   0.0115
  -9.000  -0.2286   0.09650   0.09288  -0.0719   0.9435   0.0118
  -8.750  -0.2112   0.09233   0.08867  -0.0769   0.9381   0.0126
  -8.500  -0.1944   0.08837   0.08468  -0.0818   0.9315   0.0132
  -8.250  -0.1763   0.08444   0.08072  -0.0869   0.9260   0.0135
  -8.000  -0.1611   0.08063   0.07689  -0.0915   0.9194   0.0138
  -7.750  -0.1406   0.07726   0.07349  -0.0996   0.9120   0.0171
  -7.500  -0.1277   0.07407   0.07030  -0.1046   0.9043   0.0174
  -7.000  -0.0986   0.06673   0.06288  -0.1145   0.8931   0.0176
  -6.750  -0.0832   0.06290   0.05899  -0.1189   0.8885   0.0177
  -6.250  -0.0691   0.05480   0.05083  -0.1217   0.8800   0.0148
  -6.000  -0.0536   0.05092   0.04686  -0.1249   0.8759   0.0141
  -5.750  -0.0350   0.04698   0.04278  -0.1281   0.8727   0.0137
  -5.250  -0.0001   0.04102   0.03656  -0.1313   0.8647   0.0228
  -5.000   0.0219   0.03726   0.03254  -0.1328   0.8615   0.0221
  -4.750   0.0479   0.03343   0.02827  -0.1332   0.8587   0.0163
  -4.500   0.0668   0.03036   0.02494  -0.1331   0.8550   0.0154
  -4.250   0.0891   0.02744   0.02169  -0.1330   0.8517   0.0145
  -4.000   0.1136   0.02470   0.01857  -0.1328   0.8490   0.0137
  -3.750   0.1398   0.02223   0.01566  -0.1327   0.8467   0.0131
  -3.500   0.1632   0.02011   0.01315  -0.1317   0.8434   0.0127
  -3.250   0.1880   0.01831   0.01096  -0.1309   0.8404   0.0127
  -3.000   0.2141   0.01680   0.00910  -0.1303   0.8377   0.0129
  -2.750   0.2408   0.01558   0.00764  -0.1299   0.8354   0.0135
  -2.500   0.2678   0.01461   0.00650  -0.1296   0.8334   0.0154
  -2.250   0.2905   0.01406   0.00591  -0.1288   0.8301   0.0211
  -2.000   0.3144   0.01345   0.00516  -0.1281   0.8270   0.0241
  -1.750   0.3400   0.01305   0.00462  -0.1277   0.8244   0.0281
  -1.500   0.3664   0.01262   0.00416  -0.1275   0.8220   0.0511
  -1.250   0.3881   0.01152   0.00408  -0.1272   0.8197   0.3545
  -1.000   0.3936   0.01043   0.00442  -0.1221   0.8158   0.8210
  -0.750   0.4179   0.01031   0.00436  -0.1208   0.8129   0.9169
  -0.500   0.4809   0.01014   0.00408  -0.1284   0.8118   1.0000
  -0.250   0.5061   0.01021   0.00401  -0.1281   0.8091   1.0000
   0.000   0.5330   0.01028   0.00397  -0.1281   0.8070   1.0000
   0.250   0.5538   0.01042   0.00408  -0.1269   0.8027   1.0000
   0.500   0.5783   0.01052   0.00413  -0.1264   0.7992   1.0000
   0.750   0.6046   0.01060   0.00416  -0.1263   0.7964   1.0000
   1.000   0.6324   0.01067   0.00420  -0.1265   0.7941   1.0000
   1.250   0.6544   0.01083   0.00438  -0.1256   0.7897   1.0000
   1.500   0.6792   0.01095   0.00451  -0.1252   0.7860   1.0000
   1.750   0.7060   0.01103   0.00459  -0.1251   0.7831   1.0000
   2.000   0.7342   0.01110   0.00467  -0.1254   0.7806   1.0000
   2.250   0.7554   0.01129   0.00494  -0.1243   0.7754   1.0000
   2.500   0.7810   0.01139   0.00518  -0.1240   0.7715   1.0000
   2.750   0.8087   0.01146   0.00531  -0.1241   0.7686   1.0000
   3.000   0.8319   0.01162   0.00558  -0.1234   0.7638   1.0000
   3.250   0.8564   0.01175   0.00583  -0.1228   0.7591   1.0000
   3.500   0.8826   0.01167   0.00586  -0.1224   0.7517   1.0000
   3.750   0.9019   0.01088   0.00505  -0.1194   0.7145   1.0000
   4.000   0.9210   0.01059   0.00474  -0.1169   0.6657   1.0000
   4.250   0.9188   0.01149   0.00452  -0.1100   0.4737   1.0000
   4.500   0.8900   0.01428   0.00576  -0.1000   0.2096   1.0000
   4.750   0.8772   0.01660   0.00716  -0.0934   0.0279   1.0000
   5.000   0.8887   0.01744   0.00810  -0.0904   0.0181   1.0000
   5.250   0.9012   0.01829   0.00913  -0.0875   0.0149   1.0000
   5.500   0.9128   0.01919   0.01011  -0.0849   0.0115   1.0000
   5.750   0.9206   0.02039   0.01142  -0.0817   0.0089   1.0000
   6.000   0.9309   0.02156   0.01268  -0.0789   0.0081   1.0000
   6.250   0.9426   0.02291   0.01413  -0.0763   0.0076   1.0000
   6.500   0.9593   0.02445   0.01575  -0.0745   0.0072   1.0000
   6.750   0.9860   0.02629   0.01770  -0.0741   0.0070   1.0000
   7.000   1.0275   0.02882   0.02044  -0.0761   0.0068   1.0000
   7.250   1.0696   0.03194   0.02388  -0.0782   0.0070   1.0000
   7.500   1.1000   0.03513   0.02744  -0.0783   0.0071   1.0000
   7.750   1.1226   0.03851   0.03132  -0.0771   0.0074   1.0000
   8.000   1.1385   0.04179   0.03498  -0.0751   0.0077   1.0000
   8.250   1.1495   0.04521   0.03876  -0.0725   0.0079   1.0000
   8.500   1.1554   0.04873   0.04262  -0.0694   0.0082   1.0000
   8.750   1.1574   0.05216   0.04636  -0.0661   0.0084   1.0000
   9.000   1.1542   0.05586   0.05036  -0.0623   0.0087   1.0000
   9.250   1.1456   0.05956   0.05432  -0.0582   0.0090   1.0000
   9.500   1.1332   0.06304   0.05801  -0.0539   0.0092   1.0000
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