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

WORTMANN FX 75-141 (fx75141-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 75-141 (fx75141-il)
Reynolds number: 200,000
Max Cl/Cd: 77.32 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx75141-il-200000-n5.txt
Download as CSV file: xf-fx75141-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 75-141                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5485   0.05648   0.05195  -0.1049   0.9104   0.0204
 -12.250  -0.5473   0.05053   0.04575  -0.1133   0.8994   0.0206
 -12.000  -0.5411   0.04629   0.04127  -0.1195   0.8904   0.0210
 -11.750  -0.5409   0.04215   0.03685  -0.1243   0.8820   0.0212
 -11.500  -0.5357   0.03889   0.03333  -0.1279   0.8758   0.0215
 -11.250  -0.5321   0.03623   0.03045  -0.1297   0.8702   0.0219
 -11.000  -0.5288   0.03387   0.02783  -0.1305   0.8651   0.0222
 -10.750  -0.5250   0.03199   0.02570  -0.1302   0.8609   0.0226
 -10.500  -0.5169   0.03025   0.02369  -0.1297   0.8574   0.0233
 -10.250  -0.5064   0.02864   0.02180  -0.1289   0.8537   0.0240
 -10.000  -0.4926   0.02722   0.02012  -0.1282   0.8503   0.0248
  -9.750  -0.4751   0.02630   0.01916  -0.1279   0.8474   0.0256
  -9.500  -0.4559   0.02557   0.01835  -0.1276   0.8451   0.0265
  -9.000  -0.4172   0.02371   0.01618  -0.1266   0.8408   0.0286
  -8.750  -0.3975   0.02279   0.01508  -0.1259   0.8382   0.0297
  -8.500  -0.3777   0.02194   0.01419  -0.1253   0.8356   0.0307
  -8.250  -0.3562   0.02135   0.01357  -0.1249   0.8333   0.0322
  -8.000  -0.3338   0.02076   0.01290  -0.1246   0.8313   0.0340
  -7.750  -0.3106   0.02017   0.01216  -0.1242   0.8294   0.0359
  -7.500  -0.2883   0.01947   0.01142  -0.1239   0.8274   0.0376
  -7.250  -0.2661   0.01897   0.01090  -0.1234   0.8252   0.0396
  -7.000  -0.2434   0.01852   0.01039  -0.1229   0.8229   0.0423
  -6.750  -0.2210   0.01798   0.00982  -0.1225   0.8203   0.0451
  -6.500  -0.1974   0.01754   0.00936  -0.1222   0.8178   0.0482
  -6.250  -0.1726   0.01718   0.00891  -0.1219   0.8155   0.0520
  -6.000  -0.1480   0.01670   0.00844  -0.1218   0.8132   0.0566
  -5.750  -0.1219   0.01638   0.00803  -0.1218   0.8113   0.0619
  -5.500  -0.0987   0.01599   0.00768  -0.1214   0.8086   0.0683
  -5.250  -0.0743   0.01569   0.00737  -0.1211   0.8057   0.0760
  -5.000  -0.0493   0.01537   0.00706  -0.1209   0.8029   0.0870
  -4.750  -0.0235   0.01505   0.00677  -0.1208   0.8002   0.1017
  -4.500   0.0028   0.01469   0.00648  -0.1209   0.7978   0.1230
  -4.250   0.0297   0.01435   0.00622  -0.1212   0.7957   0.1535
  -4.000   0.0541   0.01401   0.00604  -0.1210   0.7927   0.1947
  -3.750   0.0784   0.01360   0.00586  -0.1208   0.7894   0.2507
  -3.500   0.1032   0.01313   0.00568  -0.1208   0.7865   0.3283
  -3.250   0.1287   0.01273   0.00562  -0.1207   0.7837   0.4212
  -3.000   0.1556   0.01257   0.00560  -0.1206   0.7814   0.4821
  -2.750   0.1832   0.01250   0.00561  -0.1205   0.7791   0.5246
  -2.500   0.2071   0.01251   0.00573  -0.1197   0.7754   0.5567
  -2.250   0.2326   0.01256   0.00584  -0.1191   0.7719   0.5833
  -2.000   0.2594   0.01262   0.00591  -0.1187   0.7688   0.6041
  -1.750   0.2870   0.01270   0.00598  -0.1184   0.7661   0.6226
  -1.500   0.3156   0.01279   0.00604  -0.1184   0.7637   0.6399
  -1.250   0.3401   0.01291   0.00617  -0.1177   0.7595   0.6533
  -1.000   0.3662   0.01301   0.00625  -0.1172   0.7555   0.6663
  -0.750   0.3928   0.01312   0.00636  -0.1167   0.7521   0.6775
  -0.500   0.4209   0.01318   0.00639  -0.1166   0.7493   0.6874
  -0.250   0.4486   0.01323   0.00640  -0.1165   0.7462   0.6947
   0.000   0.4730   0.01329   0.00648  -0.1159   0.7411   0.7012
   0.250   0.4994   0.01331   0.00651  -0.1155   0.7369   0.7063
   0.500   0.5279   0.01330   0.00646  -0.1156   0.7336   0.7126
   0.750   0.5556   0.01329   0.00644  -0.1155   0.7301   0.7177
   1.000   0.5791   0.01335   0.00656  -0.1146   0.7242   0.7225
   1.250   0.6063   0.01334   0.00654  -0.1145   0.7198   0.7282
   1.500   0.6353   0.01328   0.00646  -0.1146   0.7164   0.7329
   1.750   0.6585   0.01334   0.00660  -0.1137   0.7100   0.7371
   2.000   0.6848   0.01333   0.00660  -0.1133   0.7048   0.7422
   2.250   0.7139   0.01326   0.00651  -0.1135   0.7007   0.7474
   2.500   0.7365   0.01332   0.00667  -0.1125   0.6933   0.7510
   2.750   0.7632   0.01327   0.00665  -0.1122   0.6877   0.7553
   3.000   0.7889   0.01328   0.00669  -0.1118   0.6812   0.7602
   3.250   0.8146   0.01326   0.00672  -0.1113   0.6739   0.7643
   3.500   0.8401   0.01322   0.00673  -0.1108   0.6661   0.7680
   3.750   0.8666   0.01310   0.00660  -0.1103   0.6557   0.7723
   4.000   0.8917   0.01300   0.00647  -0.1095   0.6405   0.7768
   4.250   0.9162   0.01296   0.00641  -0.1087   0.6247   0.7805
   4.500   0.9403   0.01300   0.00646  -0.1079   0.6117   0.7843
   4.750   0.9646   0.01308   0.00655  -0.1072   0.5996   0.7885
   5.000   0.9891   0.01320   0.00668  -0.1065   0.5874   0.7930
   5.250   1.0125   0.01333   0.00681  -0.1056   0.5747   0.7967
   5.500   1.0347   0.01349   0.00697  -0.1045   0.5604   0.8008
   5.750   1.0566   0.01369   0.00718  -0.1034   0.5460   0.8055
   6.000   1.0770   0.01393   0.00741  -0.1020   0.5285   0.8103
   6.250   1.0937   0.01421   0.00765  -0.0999   0.5040   0.8149
   6.500   1.1081   0.01457   0.00793  -0.0974   0.4751   0.8202
   6.750   1.1204   0.01501   0.00827  -0.0946   0.4436   0.8257
   7.000   1.1289   0.01549   0.00865  -0.0912   0.4111   0.8308
   7.250   1.1332   0.01608   0.00911  -0.0872   0.3761   0.8367
   7.500   1.1348   0.01689   0.00974  -0.0829   0.3375   0.8430
   7.750   1.1356   0.01782   0.01050  -0.0788   0.3007   0.8504
   8.000   1.1379   0.01883   0.01138  -0.0752   0.2682   0.8585
   8.250   1.1419   0.01990   0.01234  -0.0723   0.2384   0.8686
   8.500   1.1484   0.02097   0.01334  -0.0699   0.2128   0.8831
   8.750   1.1593   0.02204   0.01439  -0.0685   0.1897   0.9104
   9.000   1.1666   0.02306   0.01537  -0.0665   0.1710   1.0000
   9.250   1.1767   0.02422   0.01646  -0.0650   0.1526   1.0000
   9.500   1.1862   0.02544   0.01762  -0.0635   0.1345   1.0000
   9.750   1.1949   0.02674   0.01883  -0.0619   0.1168   1.0000
  10.000   1.2035   0.02808   0.02009  -0.0604   0.1015   1.0000
  10.250   1.2120   0.02944   0.02140  -0.0590   0.0877   1.0000
  10.500   1.2199   0.03089   0.02279  -0.0576   0.0769   1.0000
  10.750   1.2292   0.03225   0.02417  -0.0563   0.0689   1.0000
  11.000   1.2373   0.03372   0.02564  -0.0550   0.0628   1.0000
  11.250   1.2456   0.03521   0.02715  -0.0537   0.0576   1.0000
  11.500   1.2527   0.03682   0.02878  -0.0525   0.0535   1.0000
  11.750   1.2612   0.03833   0.03037  -0.0513   0.0500   1.0000
  12.000   1.2678   0.04004   0.03211  -0.0502   0.0470   1.0000
  12.250   1.2733   0.04189   0.03402  -0.0491   0.0447   1.0000
  12.500   1.2811   0.04357   0.03580  -0.0482   0.0422   1.0000
  12.750   1.2872   0.04545   0.03774  -0.0473   0.0400   1.0000
  13.000   1.2914   0.04757   0.03991  -0.0464   0.0384   1.0000
  13.250   1.2957   0.04974   0.04214  -0.0456   0.0368   1.0000
  13.500   1.3020   0.05176   0.04428  -0.0450   0.0353   1.0000
  13.750   1.3076   0.05392   0.04654  -0.0444   0.0338   1.0000
  14.000   1.3121   0.05623   0.04892  -0.0440   0.0323   1.0000
  14.250   1.3142   0.05888   0.05162  -0.0437   0.0312   1.0000
  14.500   1.3174   0.06145   0.05428  -0.0433   0.0302   1.0000
  14.750   1.3220   0.06393   0.05689  -0.0431   0.0291   1.0000
  15.000   1.3261   0.06651   0.05958  -0.0431   0.0279   1.0000
  15.250   1.3293   0.06925   0.06242  -0.0431   0.0270   1.0000
  15.500   1.3312   0.07223   0.06548  -0.0434   0.0261   1.0000
  15.750   1.3315   0.07543   0.06875  -0.0436   0.0255   1.0000
  16.000   1.3324   0.07860   0.07202  -0.0439   0.0248   1.0000
  16.250   1.3344   0.08172   0.07530  -0.0443   0.0241   1.0000
  16.500   1.3357   0.08499   0.07871  -0.0448   0.0235   1.0000
  16.750   1.3363   0.08841   0.08226  -0.0455   0.0228   1.0000
  17.000   1.3361   0.09197   0.08594  -0.0464   0.0222   1.0000
  17.250   1.3353   0.09570   0.08978  -0.0475   0.0216   1.0000
  17.500   1.3338   0.09958   0.09375  -0.0487   0.0212   1.0000
  17.750   1.3315   0.10362   0.09786  -0.0502   0.0207   1.0000
  18.000   1.3293   0.10767   0.10202  -0.0516   0.0202   1.0000
  18.250   1.3260   0.11208   0.10664  -0.0533   0.0198   1.0000
  18.500   1.3220   0.11667   0.11141  -0.0553   0.0193   1.0000
  18.750   1.3175   0.12139   0.11630  -0.0574   0.0189   1.0000
  19.000   1.3126   0.12627   0.12134  -0.0598   0.0186   1.0000
  19.250   1.3068   0.13138   0.12660  -0.0625   0.0183   1.0000
<< Back to WORTMANN FX 75-141 (fx75141-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 75-141 (fx75141-il)