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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 100,000
Max Cl/Cd: 36.5 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-100000-n5.txt
Download as CSV file: xf-fx74130wp2-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1707   0.10392   0.09835  -0.0945   0.8495   0.0458
 -10.250  -0.1663   0.10069   0.09513  -0.0963   0.8476   0.0470
 -10.000  -0.1627   0.09752   0.09197  -0.0983   0.8458   0.0482
  -9.750  -0.1626   0.09428   0.08875  -0.1008   0.8433   0.0497
  -9.500  -0.1703   0.09122   0.08580  -0.1057   0.8405   0.0512
  -9.250  -0.1735   0.08767   0.08230  -0.1097   0.8382   0.0515
  -9.000  -0.1800   0.08374   0.07838  -0.1141   0.8358   0.0516
  -8.500  -0.1976   0.07799   0.07253  -0.1166   0.8314   0.0518
  -8.000  -0.1326   0.05262   0.04741  -0.1136   0.8236   0.0268
  -7.750  -0.1399   0.04946   0.04424  -0.1129   0.8218   0.0261
  -7.500  -0.1802   0.05982   0.05418  -0.1172   0.8230   0.0259
  -7.250  -0.1791   0.05686   0.05108  -0.1169   0.8212   0.0252
  -7.000  -0.1761   0.05386   0.04792  -0.1164   0.8196   0.0244
  -6.750  -0.1718   0.05090   0.04478  -0.1158   0.8177   0.0237
  -6.500  -0.1667   0.04803   0.04169  -0.1147   0.8151   0.0231
  -6.250  -0.1590   0.04518   0.03857  -0.1135   0.8125   0.0223
  -6.000  -0.1484   0.04243   0.03548  -0.1122   0.8104   0.0219
  -5.750  -0.1350   0.03984   0.03252  -0.1110   0.8086   0.0215
  -5.500  -0.1184   0.03788   0.03022  -0.1100   0.8071   0.0230
  -5.250  -0.0996   0.03594   0.02787  -0.1091   0.8058   0.0241
  -5.000  -0.0807   0.03416   0.02569  -0.1079   0.8040   0.0249
  -4.750  -0.0645   0.03270   0.02392  -0.1064   0.8012   0.0249
  -4.500  -0.0450   0.03121   0.02210  -0.1051   0.7990   0.0250
  -4.250  -0.0235   0.02992   0.02049  -0.1041   0.7972   0.0252
  -4.000  -0.0006   0.02876   0.01908  -0.1032   0.7956   0.0256
  -3.750   0.0233   0.02774   0.01787  -0.1025   0.7942   0.0262
  -3.500   0.0478   0.02687   0.01686  -0.1018   0.7928   0.0270
  -3.250   0.0707   0.02584   0.01579  -0.1011   0.7915   0.0284
  -3.000   0.0844   0.02565   0.01560  -0.0993   0.7887   0.0314
  -2.750   0.0987   0.02566   0.01554  -0.0975   0.7859   0.0364
  -2.500   0.1167   0.02534   0.01514  -0.0961   0.7834   0.0419
  -2.250   0.1382   0.02498   0.01476  -0.0952   0.7814   0.0568
  -2.000   0.1545   0.02353   0.01447  -0.0940   0.7797   0.3037
  -1.500   0.1422   0.02389   0.01662  -0.0787   0.7736   0.8413
  -1.250   0.1329   0.02458   0.01736  -0.0697   0.7695   0.8968
  -1.000   0.2091   0.02492   0.01736  -0.0764   0.7706   0.9526
  -0.750   0.2402   0.02517   0.01741  -0.0778   0.7687   0.9593
  -0.500   0.2767   0.02533   0.01739  -0.0802   0.7672   0.9631
  -0.250   0.3097   0.02546   0.01735  -0.0818   0.7657   0.9669
   0.000   0.3393   0.02560   0.01735  -0.0827   0.7645   0.9709
   0.500   0.3809   0.02683   0.01846  -0.0832   0.7565   0.9810
   0.750   0.4084   0.02710   0.01865  -0.0840   0.7541   0.9847
   1.000   0.4403   0.02727   0.01875  -0.0854   0.7523   0.9873
   1.250   0.4724   0.02739   0.01881  -0.0867   0.7508   0.9900
   1.750   0.4879   0.02879   0.02021  -0.0823   0.7402   1.0000
   2.000   0.5076   0.02890   0.02029  -0.0811   0.7379   1.0000
   2.250   0.5263   0.02904   0.02041  -0.0798   0.7356   1.0000
   2.500   0.4884   0.02996   0.02134  -0.0697   0.7252   1.0000
   2.750   0.5165   0.03006   0.02142  -0.0700   0.7234   1.0000
   3.250   0.5366   0.03121   0.02258  -0.0660   0.7117   1.0000
   3.500   0.5681   0.03129   0.02268  -0.0668   0.7098   1.0000
   5.000   0.7045   0.03322   0.02493  -0.0655   0.6819   1.0000
   5.250   0.7107   0.03413   0.02590  -0.0634   0.6715   1.0000
   5.500   0.7451   0.03391   0.02583  -0.0644   0.6691   1.0000
   5.750   0.7546   0.03466   0.02666  -0.0627   0.6587   1.0000
   6.000   0.7891   0.03432   0.02645  -0.0635   0.6558   1.0000
   6.500   0.8275   0.03481   0.02723  -0.0618   0.6393   1.0000
   7.000   0.8669   0.03498   0.02768  -0.0600   0.6195   1.0000
   8.000   0.9520   0.03369   0.02709  -0.0557   0.5636   1.0000
   8.250   0.9723   0.03322   0.02676  -0.0542   0.5364   1.0000
   8.500   1.0173   0.03040   0.02389  -0.0536   0.4824   1.0000
   8.750   1.0494   0.02875   0.02144  -0.0514   0.3595   1.0000
   9.000   1.0471   0.03053   0.02269  -0.0483   0.2812   1.0000
   9.250   1.0452   0.03254   0.02423  -0.0457   0.2097   1.0000
   9.500   1.0467   0.03447   0.02578  -0.0436   0.1501   1.0000
   9.750   1.0498   0.03640   0.02737  -0.0417   0.1036   1.0000
  10.000   1.0552   0.03824   0.02902  -0.0401   0.0752   1.0000
  10.250   1.0615   0.04005   0.03078  -0.0385   0.0598   1.0000
  10.500   1.0681   0.04188   0.03262  -0.0371   0.0498   1.0000
  10.750   1.0730   0.04389   0.03462  -0.0357   0.0427   1.0000
  11.000   1.0814   0.04566   0.03654  -0.0345   0.0362   1.0000
  11.250   1.0863   0.04780   0.03871  -0.0332   0.0316   1.0000
  11.500   1.0952   0.04967   0.04081  -0.0320   0.0278   1.0000
  11.750   1.1023   0.05169   0.04289  -0.0311   0.0243   1.0000
  12.000   1.1112   0.05379   0.04509  -0.0300   0.0218   1.0000
  12.250   1.1245   0.05572   0.04723  -0.0289   0.0198   1.0000
  12.500   1.1387   0.05774   0.04942  -0.0280   0.0185   1.0000
  12.750   1.1500   0.05995   0.05178  -0.0272   0.0171   1.0000
  13.000   1.1587   0.06249   0.05442  -0.0266   0.0159   1.0000
  13.250   1.1674   0.06542   0.05762  -0.0258   0.0149   1.0000
  13.500   1.1729   0.06839   0.06093  -0.0251   0.0141   1.0000
  13.750   1.1750   0.07184   0.06471  -0.0244   0.0135   1.0000
  14.000   1.1728   0.07579   0.06900  -0.0239   0.0132   1.0000
  14.250   1.1666   0.08016   0.07369  -0.0236   0.0130   1.0000
  14.500   1.1572   0.08486   0.07870  -0.0237   0.0128   1.0000
  14.750   1.1449   0.09003   0.08417  -0.0242   0.0128   1.0000
  15.000   1.1305   0.09565   0.09008  -0.0253   0.0127   1.0000
  15.250   1.1144   0.10181   0.09650  -0.0271   0.0127   1.0000
  15.500   1.0968   0.10856   0.10351  -0.0297   0.0127   1.0000
  15.750   1.0783   0.11595   0.11113  -0.0332   0.0128   1.0000
  16.000   1.0591   0.12412   0.11950  -0.0377   0.0130   1.0000
  16.250   1.0388   0.13337   0.12894  -0.0433   0.0131   1.0000
  16.500   1.0185   0.14368   0.13940  -0.0500   0.0134   1.0000
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