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WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 74-080 (fx74080-il)
Reynolds number: 200,000
Max Cl/Cd: 80.33 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74080-il-200000.txt
Download as CSV file: xf-fx74080-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3320   0.12308   0.11965  -0.0431   1.0000   0.0169
 -10.250  -0.3545   0.12402   0.12073  -0.0368   1.0000   0.0168
 -10.000  -0.3588   0.12232   0.11906  -0.0357   0.9991   0.0173
  -9.750  -0.3454   0.11825   0.11499  -0.0395   0.9963   0.0178
  -9.500  -0.3328   0.11439   0.11112  -0.0431   0.9933   0.0185
  -9.250  -0.3196   0.11053   0.10726  -0.0469   0.9904   0.0191
  -9.000  -0.3064   0.10664   0.10336  -0.0508   0.9875   0.0200
  -8.750  -0.2942   0.10303   0.09975  -0.0544   0.9835   0.0206
  -8.500  -0.2798   0.09944   0.09616  -0.0592   0.9800   0.0217
  -8.250  -0.2635   0.09606   0.09278  -0.0656   0.9771   0.0225
  -8.000  -0.2535   0.09336   0.09010  -0.0707   0.9712   0.0229
  -7.750  -0.2386   0.09002   0.08670  -0.0767   0.9666   0.0232
  -7.500  -0.2178   0.08569   0.08236  -0.0841   0.9637   0.0233
  -7.250  -0.2066   0.08232   0.07899  -0.0889   0.9570   0.0234
  -7.000  -0.1848   0.07796   0.07458  -0.0957   0.9536   0.0234
  -6.750  -0.1602   0.07220   0.06877  -0.1038   0.9513   0.0237
  -6.500  -0.1624   0.06682   0.06344  -0.1022   0.9474   0.0252
  -6.250  -0.1504   0.06368   0.06028  -0.1037   0.9427   0.0262
  -6.000  -0.1271   0.05969   0.05622  -0.1087   0.9399   0.0287
  -5.750  -0.0949   0.05515   0.05155  -0.1163   0.9377   0.0326
  -5.500  -0.0778   0.05310   0.04929  -0.1187   0.9303   0.0354
  -5.250  -0.0531   0.04779   0.04370  -0.1235   0.9266   0.0373
  -5.000  -0.0315   0.04415   0.04007  -0.1256   0.9248   0.0394
  -4.750  -0.0236   0.04228   0.03812  -0.1239   0.9187   0.0417
  -4.500   0.0011   0.03955   0.03516  -0.1254   0.9150   0.0460
  -4.250   0.0345   0.03598   0.03108  -0.1284   0.9124   0.0512
  -4.000   0.0634   0.03312   0.02816  -0.1305   0.9108   0.0554
  -3.500   0.0974   0.02966   0.02419  -0.1281   0.9010   0.0681
  -3.250   0.1292   0.02756   0.02180  -0.1297   0.8991   0.0812
  -3.000   0.1622   0.02573   0.01974  -0.1314   0.8975   0.0975
  -2.750   0.1820   0.02290   0.01603  -0.1259   0.8914   0.0347
  -2.500   0.2109   0.02073   0.01351  -0.1259   0.8886   0.0319
  -2.250   0.2447   0.01976   0.01222  -0.1266   0.8866   0.0355
  -2.000   0.2778   0.01815   0.01042  -0.1273   0.8850   0.0377
  -1.750   0.2937   0.01755   0.00981  -0.1251   0.8800   0.0389
  -1.500   0.3162   0.01694   0.00915  -0.1241   0.8757   0.0441
  -1.250   0.3460   0.01602   0.00832  -0.1245   0.8733   0.0927
  -1.000   0.3877   0.01340   0.00819  -0.1268   0.8732   1.0000
  -0.750   0.4204   0.01343   0.00800  -0.1279   0.8712   1.0000
  -0.500   0.4310   0.01391   0.00838  -0.1250   0.8641   1.0000
  -0.250   0.4598   0.01400   0.00834  -0.1253   0.8609   1.0000
   0.000   0.4927   0.01403   0.00823  -0.1265   0.8587   1.0000
   0.250   0.5098   0.01443   0.00856  -0.1247   0.8528   1.0000
   0.500   0.5347   0.01462   0.00869  -0.1244   0.8485   1.0000
   0.750   0.5664   0.01467   0.00868  -0.1253   0.8460   1.0000
   1.000   0.5999   0.01470   0.00866  -0.1264   0.8441   1.0000
   1.250   0.6104   0.01527   0.00926  -0.1236   0.8358   1.0000
   1.500   0.6415   0.01533   0.00930  -0.1243   0.8331   1.0000
   1.750   0.6749   0.01534   0.00931  -0.1254   0.8311   1.0000
   2.000   0.6866   0.01593   0.00992  -0.1228   0.8229   1.0000
   2.250   0.7177   0.01597   0.01000  -0.1235   0.8200   1.0000
   2.500   0.7513   0.01596   0.01003  -0.1246   0.8179   1.0000
   2.750   0.7629   0.01658   0.01079  -0.1220   0.8094   1.0000
   3.000   0.7948   0.01657   0.01086  -0.1228   0.8065   1.0000
   3.250   0.8289   0.01652   0.01092  -0.1239   0.8044   1.0000
   3.500   0.8413   0.01709   0.01160  -0.1214   0.7953   1.0000
   3.750   0.8842   0.01571   0.01035  -0.1224   0.7849   1.0000
   4.000   0.9342   0.01163   0.00629  -0.1212   0.7373   1.0000
   4.250   0.9186   0.01156   0.00477  -0.1096   0.4651   1.0000
   4.500   0.8891   0.01443   0.00607  -0.0996   0.1936   1.0000
   4.750   0.8777   0.01670   0.00743  -0.0929   0.0383   1.0000
   5.000   0.8892   0.01757   0.00846  -0.0898   0.0313   1.0000
   5.250   0.8970   0.01868   0.00969  -0.0861   0.0277   1.0000
   5.500   0.9009   0.02014   0.01123  -0.0820   0.0262   1.0000
   5.750   0.9092   0.02186   0.01298  -0.0787   0.0251   1.0000
   6.000   0.9290   0.02315   0.01433  -0.0773   0.0244   1.0000
   6.250   0.9545   0.02447   0.01573  -0.0766   0.0208   1.0000
   6.500   1.0153   0.02804   0.01947  -0.0815   0.0222   1.0000
  10.250   1.0322   0.07189   0.06805  -0.0356   0.0356   1.0000
  10.500   1.0091   0.07615   0.07247  -0.0336   0.0356   1.0000
  10.750   0.9860   0.08097   0.07743  -0.0324   0.0358   1.0000
  11.000   0.9635   0.08615   0.08273  -0.0320   0.0360   1.0000
  11.250   0.9421   0.09155   0.08824  -0.0323   0.0363   1.0000
  11.500   0.9202   0.09723   0.09402  -0.0332   0.0365   1.0000
  11.750   0.8950   0.10255   0.09945  -0.0347   0.0368   1.0000
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