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USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USNPS4 (smoothed) (usnps4-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.32 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usnps4-il-1000000-n5.txt
Download as CSV file: xf-usnps4-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USNPS4 (smoothed)                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3394   0.02062   0.01716  -0.1296   0.9562   0.0103
  -8.750  -0.3157   0.01834   0.01457  -0.1300   0.9541   0.0107
  -8.500  -0.2886   0.01683   0.01282  -0.1307   0.9525   0.0109
  -8.250  -0.2597   0.01567   0.01146  -0.1315   0.9511   0.0112
  -8.000  -0.2343   0.01486   0.01050  -0.1313   0.9480   0.0113
  -7.750  -0.2105   0.01406   0.00956  -0.1307   0.9435   0.0116
  -7.500  -0.1821   0.01337   0.00878  -0.1310   0.9405   0.0119
  -7.250  -0.1506   0.01286   0.00820  -0.1320   0.9381   0.0121
  -7.000  -0.1228   0.01246   0.00774  -0.1321   0.9340   0.0124
  -6.750  -0.0954   0.01206   0.00728  -0.1321   0.9286   0.0127
  -6.500  -0.0638   0.01165   0.00680  -0.1330   0.9243   0.0131
  -6.250  -0.0358   0.01128   0.00636  -0.1330   0.9177   0.0135
  -6.000  -0.0055   0.01089   0.00587  -0.1336   0.9108   0.0139
  -5.750   0.0233   0.01053   0.00542  -0.1338   0.9023   0.0141
  -5.500   0.0530   0.01016   0.00495  -0.1342   0.8929   0.0144
  -5.250   0.0814   0.00977   0.00448  -0.1343   0.8810   0.0149
  -5.000   0.1096   0.00954   0.00417  -0.1344   0.8673   0.0153
  -4.750   0.1374   0.00936   0.00391  -0.1343   0.8516   0.0157
  -4.500   0.1645   0.00922   0.00367  -0.1341   0.8342   0.0162
  -4.250   0.1911   0.00911   0.00345  -0.1337   0.8154   0.0168
  -4.000   0.2172   0.00902   0.00324  -0.1333   0.7952   0.0173
  -3.750   0.2427   0.00895   0.00305  -0.1327   0.7743   0.0177
  -3.500   0.2680   0.00883   0.00283  -0.1321   0.7528   0.0184
  -3.250   0.2931   0.00880   0.00269  -0.1315   0.7300   0.0191
  -3.000   0.3183   0.00880   0.00259  -0.1309   0.7077   0.0198
  -2.750   0.3436   0.00880   0.00248  -0.1303   0.6847   0.0207
  -2.500   0.3686   0.00884   0.00240  -0.1296   0.6614   0.0215
  -2.250   0.3939   0.00884   0.00231  -0.1291   0.6380   0.0230
  -2.000   0.4190   0.00890   0.00227  -0.1285   0.6149   0.0245
  -1.750   0.4445   0.00896   0.00221  -0.1280   0.5918   0.0259
  -1.500   0.4698   0.00902   0.00218  -0.1274   0.5689   0.0281
  -1.250   0.4955   0.00909   0.00217  -0.1270   0.5470   0.0304
  -1.000   0.5210   0.00917   0.00216  -0.1265   0.5252   0.0333
  -0.750   0.5467   0.00926   0.00217  -0.1261   0.5046   0.0367
  -0.500   0.5725   0.00935   0.00218  -0.1257   0.4846   0.0406
  -0.250   0.5982   0.00945   0.00220  -0.1253   0.4647   0.0445
   0.000   0.6241   0.00954   0.00223  -0.1249   0.4471   0.0503
   0.250   0.6500   0.00964   0.00227  -0.1246   0.4305   0.0573
   0.500   0.6757   0.00974   0.00232  -0.1242   0.4134   0.0662
   0.750   0.7016   0.00983   0.00238  -0.1238   0.3983   0.0801
   1.000   0.7276   0.00988   0.00244  -0.1236   0.3850   0.1101
   1.500   0.7682   0.00834   0.00287  -0.1211   0.3599   0.9158
   1.750   0.7995   0.00843   0.00294  -0.1218   0.3473   1.0000
   2.000   0.8251   0.00858   0.00301  -0.1214   0.3366   1.0000
   2.250   0.8505   0.00875   0.00310  -0.1210   0.3259   1.0000
   2.500   0.8757   0.00894   0.00320  -0.1205   0.3152   1.0000
   2.750   0.9011   0.00910   0.00330  -0.1201   0.3056   1.0000
   3.000   0.9266   0.00927   0.00341  -0.1197   0.2979   1.0000
   3.250   0.9517   0.00945   0.00353  -0.1192   0.2889   1.0000
   3.500   0.9769   0.00963   0.00365  -0.1188   0.2807   1.0000
   4.000   1.0267   0.00999   0.00391  -0.1178   0.2659   1.0000
   4.250   1.0513   0.01018   0.00406  -0.1173   0.2590   1.0000
   4.500   1.0761   0.01036   0.00421  -0.1168   0.2533   1.0000
   4.750   1.1004   0.01056   0.00436  -0.1162   0.2463   1.0000
   5.000   1.1243   0.01077   0.00454  -0.1156   0.2398   1.0000
   5.250   1.1485   0.01095   0.00470  -0.1150   0.2341   1.0000
   5.500   1.1715   0.01117   0.00488  -0.1142   0.2285   1.0000
   5.750   1.1946   0.01136   0.00506  -0.1133   0.2242   1.0000
   6.000   1.2175   0.01156   0.00526  -0.1125   0.2196   1.0000
   6.250   1.2396   0.01181   0.00547  -0.1115   0.2142   1.0000
   6.500   1.2621   0.01203   0.00568  -0.1106   0.2098   1.0000
   6.750   1.2845   0.01226   0.00591  -0.1097   0.2049   1.0000
   7.000   1.3064   0.01252   0.00615  -0.1088   0.2004   1.0000
   7.250   1.3287   0.01276   0.00640  -0.1079   0.1967   1.0000
   7.500   1.3511   0.01299   0.00664  -0.1071   0.1935   1.0000
   7.750   1.3730   0.01325   0.00690  -0.1061   0.1897   1.0000
   8.000   1.3940   0.01355   0.00719  -0.1051   0.1857   1.0000
   8.250   1.4155   0.01383   0.00748  -0.1041   0.1824   1.0000
   8.500   1.4371   0.01410   0.00777  -0.1032   0.1789   1.0000
   8.750   1.4580   0.01440   0.00808  -0.1021   0.1753   1.0000
   9.000   1.4782   0.01475   0.00843  -0.1010   0.1719   1.0000
   9.250   1.4987   0.01507   0.00877  -0.0999   0.1691   1.0000
   9.500   1.5195   0.01536   0.00911  -0.0989   0.1669   1.0000
   9.750   1.5398   0.01569   0.00946  -0.0978   0.1642   1.0000
  10.000   1.5585   0.01611   0.00988  -0.0965   0.1597   1.0000
  10.250   1.5769   0.01654   0.01031  -0.0952   0.1534   1.0000
  10.500   1.5947   0.01701   0.01077  -0.0938   0.1472   1.0000
  10.750   1.6121   0.01749   0.01126  -0.0923   0.1428   1.0000
  11.000   1.6303   0.01793   0.01172  -0.0911   0.1387   1.0000
  11.250   1.6469   0.01847   0.01226  -0.0896   0.1335   1.0000
  11.500   1.6633   0.01902   0.01283  -0.0880   0.1286   1.0000
  11.750   1.6786   0.01963   0.01344  -0.0864   0.1222   1.0000
  12.000   1.6927   0.02032   0.01412  -0.0846   0.1154   1.0000
  12.250   1.7039   0.02119   0.01496  -0.0825   0.1058   1.0000
  12.500   1.7133   0.02220   0.01591  -0.0802   0.0945   1.0000
  12.750   1.7187   0.02347   0.01711  -0.0774   0.0795   1.0000
  13.000   1.7174   0.02523   0.01875  -0.0739   0.0614   1.0000
  13.250   1.7084   0.02760   0.02100  -0.0697   0.0404   1.0000
  13.500   1.7058   0.02962   0.02299  -0.0666   0.0291   1.0000
  13.750   1.7069   0.03144   0.02483  -0.0641   0.0228   1.0000
  14.000   1.7098   0.03321   0.02664  -0.0620   0.0188   1.0000
  14.250   1.7135   0.03498   0.02845  -0.0602   0.0164   1.0000
  14.500   1.7170   0.03683   0.03035  -0.0585   0.0145   1.0000
  14.750   1.7209   0.03873   0.03232  -0.0570   0.0132   1.0000
  15.000   1.7242   0.04077   0.03443  -0.0557   0.0120   1.0000
  15.250   1.7256   0.04307   0.03680  -0.0545   0.0110   1.0000
  15.500   1.7279   0.04536   0.03917  -0.0534   0.0103   1.0000
  15.750   1.7284   0.04791   0.04180  -0.0525   0.0097   1.0000
  16.000   1.7275   0.05073   0.04470  -0.0518   0.0091   1.0000
  16.250   1.7249   0.05383   0.04789  -0.0512   0.0086   1.0000
  16.500   1.7226   0.05701   0.05117  -0.0509   0.0082   1.0000
  16.750   1.7188   0.06045   0.05471  -0.0507   0.0078   1.0000
  17.000   1.7131   0.06423   0.05860  -0.0507   0.0075   1.0000
  17.250   1.7054   0.06838   0.06284  -0.0510   0.0072   1.0000
  17.500   1.6956   0.07294   0.06751  -0.0515   0.0069   1.0000
  17.750   1.6838   0.07787   0.07256  -0.0522   0.0067   1.0000
  18.000   1.6699   0.08318   0.07798  -0.0531   0.0065   1.0000
  18.250   1.6564   0.08855   0.08349  -0.0543   0.0063   1.0000
  18.500   1.6418   0.09418   0.08925  -0.0557   0.0062   1.0000
  18.750   1.6252   0.10017   0.09537  -0.0573   0.0062   1.0000
  19.000   1.6074   0.10642   0.10174  -0.0591   0.0060   1.0000
  19.250   1.5897   0.11275   0.10820  -0.0612   0.0060   1.0000
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