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NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il)
Reynolds number: 100,000
Max Cl/Cd: 26.7 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20412-il-100000.txt
Download as CSV file: xf-sc20412-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0412 AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6045   0.10990   0.10422  -0.0167   1.0000   0.1722
 -10.250  -0.5742   0.10823   0.10250  -0.0131   1.0000   0.1772
 -10.000  -0.8191   0.06488   0.05849  -0.0464   1.0000   0.0932
  -9.750  -0.8185   0.06022   0.05372  -0.0462   1.0000   0.0918
  -9.500  -0.8231   0.05553   0.04879  -0.0458   1.0000   0.0904
  -9.250  -0.8253   0.05095   0.04387  -0.0452   1.0000   0.0892
  -9.000  -0.8214   0.04702   0.03955  -0.0446   1.0000   0.0893
  -8.750  -0.8124   0.04368   0.03581  -0.0440   1.0000   0.0907
  -8.500  -0.7994   0.04061   0.03226  -0.0435   1.0000   0.0923
  -8.250  -0.7825   0.03790   0.02907  -0.0430   1.0000   0.0936
  -8.000  -0.7642   0.03497   0.02586  -0.0426   1.0000   0.0957
  -7.750  -0.7437   0.03325   0.02418  -0.0420   1.0000   0.0992
  -7.500  -0.7222   0.03161   0.02237  -0.0413   1.0000   0.1028
  -7.250  -0.6998   0.02997   0.02041  -0.0407   1.0000   0.1061
  -7.000  -0.6779   0.02819   0.01850  -0.0400   1.0000   0.1103
  -6.750  -0.6560   0.02692   0.01727  -0.0392   1.0000   0.1150
  -6.500  -0.6331   0.02579   0.01601  -0.0384   1.0000   0.1202
  -6.250  -0.6110   0.02451   0.01471  -0.0374   1.0000   0.1260
  -6.000  -0.5888   0.02354   0.01382  -0.0365   1.0000   0.1328
  -5.750  -0.5663   0.02256   0.01281  -0.0355   1.0000   0.1406
  -5.500  -0.5441   0.02169   0.01206  -0.0346   1.0000   0.1505
  -5.250  -0.5219   0.02077   0.01129  -0.0338   1.0000   0.1620
  -5.000  -0.4989   0.01992   0.01061  -0.0332   1.0000   0.1786
  -4.750  -0.4749   0.01900   0.00992  -0.0328   1.0000   0.2051
  -4.500  -0.4467   0.01735   0.00903  -0.0343   1.0000   0.2814
  -4.250  -0.4315   0.01681   0.01043  -0.0307   1.0000   0.5789
  -4.000  -0.4126   0.01798   0.01152  -0.0275   1.0000   0.6394
  -3.750  -0.3996   0.01916   0.01266  -0.0228   1.0000   0.6647
  -3.500  -0.3873   0.02019   0.01365  -0.0181   1.0000   0.6834
  -3.250  -0.3746   0.02105   0.01448  -0.0137   1.0000   0.7002
  -3.000  -0.3610   0.02177   0.01515  -0.0097   1.0000   0.7164
  -2.750  -0.3473   0.02240   0.01573  -0.0059   1.0000   0.7328
  -2.500  -0.3332   0.02294   0.01624  -0.0023   1.0000   0.7490
  -2.250  -0.3260   0.02340   0.01671   0.0033   1.0000   0.7608
  -2.000  -0.3143   0.02368   0.01696   0.0073   1.0000   0.7747
  -1.750  -0.3035   0.02390   0.01717   0.0114   1.0000   0.7903
  -1.500  -0.2938   0.02405   0.01731   0.0158   1.0000   0.8072
  -1.250  -0.2843   0.02409   0.01735   0.0201   1.0000   0.8249
  -1.000  -0.2735   0.02400   0.01725   0.0237   1.0000   0.8417
  -0.750  -0.2604   0.02379   0.01702   0.0266   1.0000   0.8558
  -0.500  -0.2434   0.02355   0.01676   0.0282   1.0000   0.8670
  -0.250  -0.2212   0.02343   0.01661   0.0282   1.0000   0.8763
   0.000  -0.2020   0.02314   0.01631   0.0290   1.0000   0.8824
   0.250  -0.1782   0.02304   0.01619   0.0285   1.0000   0.8883
   0.500  -0.1529   0.02299   0.01614   0.0276   1.0000   0.8934
   0.750  -0.1304   0.02287   0.01604   0.0274   0.9998   0.8981
   1.000  -0.0811   0.02310   0.01627   0.0222   0.9899   0.9019
   1.250  -0.0294   0.02336   0.01655   0.0165   0.9788   0.9051
   1.500   0.0191   0.02344   0.01668   0.0117   0.9670   0.9079
   1.750   0.0684   0.02336   0.01665   0.0073   0.9519   0.9105
   2.000   0.1304   0.02296   0.01633   0.0014   0.9298   0.9122
   2.250   0.1938   0.02229   0.01576  -0.0041   0.9103   0.9141
   2.500   0.2522   0.02153   0.01512  -0.0087   0.8931   0.9160
   2.750   0.3037   0.02055   0.01427  -0.0115   0.8716   0.9175
   3.000   0.3495   0.01950   0.01334  -0.0130   0.8471   0.9191
   3.250   0.3886   0.01846   0.01240  -0.0131   0.8164   0.9208
   3.500   0.4232   0.01747   0.01146  -0.0122   0.7712   0.9229
   3.750   0.4494   0.01683   0.01070  -0.0101   0.6809   0.9258
   4.000   0.4625   0.01776   0.01009  -0.0058   0.3996   0.9288
   4.250   0.4747   0.01932   0.01064  -0.0037   0.2635   0.9319
   4.500   0.4952   0.02023   0.01117  -0.0028   0.2174   0.9349
   4.750   0.5178   0.02105   0.01170  -0.0023   0.1924   0.9382
   5.000   0.5440   0.02187   0.01236  -0.0023   0.1748   0.9412
   5.250   0.5719   0.02271   0.01309  -0.0027   0.1608   0.9440
   5.500   0.6009   0.02357   0.01400  -0.0033   0.1497   0.9467
   5.750   0.6296   0.02459   0.01495  -0.0037   0.1406   0.9496
   6.000   0.6580   0.02544   0.01584  -0.0041   0.1322   0.9531
   6.250   0.6870   0.02672   0.01718  -0.0046   0.1252   0.9570
   6.500   0.7152   0.02773   0.01833  -0.0050   0.1186   0.9610
   6.750   0.7440   0.02940   0.01997  -0.0057   0.1128   0.9649
   7.000   0.7710   0.03077   0.02177  -0.0058   0.1082   0.9691
   7.250   0.7991   0.03211   0.02320  -0.0064   0.1030   0.9736
   7.500   0.8266   0.03458   0.02577  -0.0073   0.0991   0.9788
   7.750   0.8508   0.03683   0.02862  -0.0072   0.0965   0.9851
   8.000   0.8736   0.03932   0.03159  -0.0073   0.0932   0.9949
   8.250   0.8953   0.04164   0.03416  -0.0075   0.0904   1.0000
   8.500   0.9147   0.04479   0.03762  -0.0076   0.0893   1.0000
   8.750   0.9361   0.04806   0.04102  -0.0082   0.0879   1.0000
   9.000   0.9500   0.05287   0.04609  -0.0085   0.0869   1.0000
   9.250   0.9560   0.05742   0.05110  -0.0079   0.0866   1.0000
   9.500   0.9639   0.06186   0.05592  -0.0077   0.0872   1.0000
  10.000   0.7211   0.11038   0.10622  -0.0350   0.1653   1.0000
  10.250   0.6163   0.10699   0.10299  -0.0111   0.1755   1.0000
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