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FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-270 (fx77w270-il)
Reynolds number: 100,000
Max Cl/Cd: 1.26 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w270-il-100000.txt
Download as CSV file: xf-fx77w270-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-270                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.4301   0.17566   0.16987   0.0034   0.6156   0.1389
 -14.750  -0.7642   0.09227   0.08576  -0.0424   0.6517   0.0720
 -14.500  -0.7870   0.08669   0.07995  -0.0436   0.6489   0.0716
 -14.250  -0.8111   0.08142   0.07440  -0.0443   0.6463   0.0712
 -14.000  -0.8344   0.07656   0.06924  -0.0444   0.6437   0.0709
 -13.750  -0.8545   0.07214   0.06456  -0.0440   0.6405   0.0707
 -13.500  -0.8710   0.06823   0.06037  -0.0432   0.6370   0.0706
 -13.250  -0.8837   0.06480   0.05664  -0.0420   0.6334   0.0705
 -13.000  -0.8936   0.06189   0.05343  -0.0403   0.6300   0.0706
 -12.750  -0.9007   0.05954   0.05078  -0.0381   0.6269   0.0707
 -12.500  -0.8993   0.05730   0.04819  -0.0366   0.6237   0.0710
 -12.250  -0.8923   0.05511   0.04573  -0.0355   0.6203   0.0714
 -12.000  -0.8822   0.05307   0.04339  -0.0346   0.6166   0.0719
 -11.750  -0.8636   0.05129   0.04143  -0.0343   0.6128   0.0725
 -11.500  -0.8358   0.04999   0.04013  -0.0347   0.6088   0.0735
 -11.250  -0.8115   0.04882   0.03889  -0.0347   0.6056   0.0747
 -11.000  -0.7900   0.04765   0.03753  -0.0344   0.6028   0.0761
 -10.750  -0.7692   0.04634   0.03601  -0.0343   0.6001   0.0776
 -10.500  -0.7402   0.04545   0.03527  -0.0349   0.5971   0.0796
 -10.250  -0.7158   0.04462   0.03442  -0.0351   0.5943   0.0819
 -10.000  -0.6916   0.04369   0.03340  -0.0351   0.5916   0.0844
  -9.750  -0.6655   0.04303   0.03281  -0.0353   0.5892   0.0873
  -9.500  -0.6417   0.04225   0.03187  -0.0352   0.5870   0.0905
  -9.250  -0.6144   0.04161   0.03133  -0.0353   0.5847   0.0940
  -9.000  -0.5895   0.04100   0.03064  -0.0351   0.5825   0.0983
  -8.750  -0.5636   0.04041   0.03009  -0.0352   0.5802   0.1036
  -8.500  -0.5362   0.03979   0.02971  -0.0354   0.5778   0.1093
  -8.250  -0.5115   0.03925   0.02936  -0.0353   0.5758   0.1157
  -8.000  -0.4890   0.03877   0.02901  -0.0351   0.5740   0.1229
  -7.750  -0.4676   0.03831   0.02868  -0.0349   0.5724   0.1318
  -7.500  -0.4476   0.03779   0.02830  -0.0346   0.5708   0.1444
  -7.250  -0.4296   0.03711   0.02785  -0.0341   0.5694   0.1616
  -7.000  -0.4127   0.03628   0.02737  -0.0339   0.5681   0.1929
  -6.750  -0.3990   0.03482   0.02658  -0.0341   0.5667   0.2635
  -6.500  -0.3850   0.03355   0.02654  -0.0337   0.5650   0.4205
  -6.250  -0.3613   0.03646   0.03002  -0.0278   0.5629   0.5101
  -6.000  -0.3311   0.03838   0.03185  -0.0271   0.5607   0.5506
  -5.750  -0.2990   0.03959   0.03299  -0.0293   0.5584   0.5819
  -5.500  -0.2684   0.04163   0.03499  -0.0295   0.5560   0.6011
  -5.250  -0.2392   0.04355   0.03685  -0.0298   0.5540   0.6197
  -5.000  -0.2115   0.04623   0.03956  -0.0273   0.5524   0.6264
  -4.750  -0.1852   0.04794   0.04122  -0.0273   0.5509   0.6418
  -4.500  -0.1582   0.05034   0.04364  -0.0252   0.5495   0.6496
  -4.250  -0.1346   0.05175   0.04501  -0.0252   0.5482   0.6630
  -4.000  -0.1090   0.05376   0.04701  -0.0236   0.5470   0.6708
  -3.750  -0.0887   0.05518   0.04840  -0.0235   0.5461   0.6844
  -3.500  -0.0638   0.05694   0.05013  -0.0215   0.5446   0.6947
  -3.250  -0.0404   0.05776   0.05083  -0.0194   0.5429   0.7078
  -3.000  -0.2835   0.07674   0.07104  -0.0267   0.6328   0.6896
  -2.750  -0.2576   0.07808   0.07225  -0.0266   0.6284   0.7040
  -2.500  -0.2346   0.07998   0.07411  -0.0225   0.6258   0.7130
  -2.250  -0.2463   0.08088   0.07493  -0.0214   0.6131   0.7246
  -2.000  -0.2375   0.08205   0.07609  -0.0155   0.6084   0.7326
  -1.750  -0.2082   0.08346   0.07737  -0.0159   0.6057   0.7477
  -1.500  -0.1849   0.08505   0.07891  -0.0121   0.6040   0.7575
  -1.250  -0.2114   0.08543   0.07928  -0.0089   0.5898   0.7644
  -1.000  -0.1934   0.08627   0.08005  -0.0058   0.5862   0.7757
  -0.750  -0.1627   0.08782   0.08149  -0.0061   0.5840   0.7916
  -0.500  -0.1889   0.08849   0.08219  -0.0005   0.5752   0.7968
  -0.250  -0.1779   0.08927   0.08292   0.0015   0.5688   0.8086
   0.000  -0.1591   0.08991   0.08348   0.0035   0.5656   0.8188
   0.250  -0.1304   0.09116   0.08464   0.0037   0.5635   0.8288
   0.500  -0.0913   0.09300   0.08636   0.0014   0.5621   0.8361
   0.750  -0.0552   0.09504   0.08830   0.0010   0.5613   0.8410
   1.000  -0.1119   0.09362   0.08696   0.0065   0.5454   0.8439
   1.250  -0.0791   0.09505   0.08829   0.0046   0.5434   0.8470
   1.500  -0.0401   0.09703   0.09017   0.0017   0.5420   0.8490
   1.750   0.0031   0.09968   0.09270  -0.0017   0.5411   0.8509
   2.000  -0.0477   0.09900   0.09211   0.0017   0.5262   0.8523
   2.250  -0.0140   0.10074   0.09376  -0.0011   0.5237   0.8544
   2.500   0.0230   0.10281   0.09574  -0.0038   0.5221   0.8565
   2.750   0.0570   0.10490   0.09776  -0.0049   0.5211   0.8590
   3.000   0.0963   0.10789   0.10068  -0.0070   0.5204   0.8612
   3.250   0.0348   0.10634   0.09923  -0.0032   0.5051   0.8618
   3.500   0.0664   0.10812   0.10095  -0.0050   0.5028   0.8635
   3.750   0.1025   0.11045   0.10321  -0.0072   0.5014   0.8655
   4.000   0.1425   0.11344   0.10614  -0.0100   0.5004   0.8668
   4.250   0.0901   0.11333   0.10613  -0.0077   0.4886   0.8670
   4.500   0.1145   0.11508   0.10783  -0.0096   0.4853   0.8678
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