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

NASA SC(2)-0518 AIRFOIL (sc20518-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0518 AIRFOIL (sc20518-il)
Reynolds number: 100,000
Max Cl/Cd: 25.92 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20518-il-100000.txt
Download as CSV file: xf-sc20518-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0518 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6674   0.09721   0.09053  -0.0576   1.0000   0.1282
 -13.250  -0.7426   0.08201   0.07513  -0.0646   1.0000   0.1254
 -13.000  -0.8187   0.07098   0.06383  -0.0680   1.0000   0.1234
 -12.750  -0.8722   0.06437   0.05697  -0.0680   1.0000   0.1225
 -12.500  -0.9109   0.06009   0.05248  -0.0660   1.0000   0.1223
 -12.250  -0.9432   0.05711   0.04933  -0.0624   1.0000   0.1224
 -12.000  -0.9705   0.05472   0.04680  -0.0583   1.0000   0.1227
 -11.750  -0.9877   0.05230   0.04418  -0.0553   1.0000   0.1234
 -11.500  -0.9997   0.05007   0.04174  -0.0524   1.0000   0.1244
 -11.250  -1.0082   0.04797   0.03937  -0.0496   1.0000   0.1257
 -11.000  -1.0140   0.04601   0.03708  -0.0470   1.0000   0.1271
 -10.750  -1.0064   0.04396   0.03492  -0.0452   1.0000   0.1289
 -10.500  -0.9925   0.04258   0.03358  -0.0438   1.0000   0.1310
 -10.250  -0.9796   0.04134   0.03232  -0.0422   1.0000   0.1333
 -10.000  -0.9687   0.04001   0.03087  -0.0406   1.0000   0.1357
  -9.750  -0.9584   0.03864   0.02926  -0.0392   1.0000   0.1383
  -9.500  -0.9461   0.03724   0.02763  -0.0379   1.0000   0.1407
  -9.250  -0.9283   0.03603   0.02656  -0.0365   1.0000   0.1435
  -9.000  -0.9119   0.03509   0.02563  -0.0353   1.0000   0.1465
  -8.750  -0.8956   0.03415   0.02459  -0.0342   1.0000   0.1501
  -8.500  -0.8788   0.03323   0.02344  -0.0333   1.0000   0.1535
  -8.250  -0.8602   0.03225   0.02265  -0.0318   1.0000   0.1571
  -8.000  -0.8420   0.03153   0.02200  -0.0307   1.0000   0.1613
  -7.750  -0.8235   0.03081   0.02116  -0.0298   1.0000   0.1662
  -7.500  -0.8053   0.03003   0.02049  -0.0285   1.0000   0.1710
  -7.250  -0.7870   0.02942   0.01999  -0.0273   1.0000   0.1765
  -7.000  -0.7674   0.02884   0.01931  -0.0266   1.0000   0.1830
  -6.750  -0.7501   0.02820   0.01893  -0.0251   1.0000   0.1901
  -6.500  -0.7303   0.02766   0.01839  -0.0245   1.0000   0.1995
  -6.250  -0.7119   0.02707   0.01804  -0.0235   1.0000   0.2099
  -6.000  -0.6923   0.02649   0.01766  -0.0228   1.0000   0.2235
  -5.750  -0.6711   0.02585   0.01727  -0.0227   1.0000   0.2433
  -5.500  -0.6468   0.02496   0.01678  -0.0237   1.0000   0.2779
  -5.250  -0.6134   0.02334   0.01634  -0.0274   1.0000   0.3923
  -5.000  -0.6041   0.02468   0.01845  -0.0222   1.0000   0.4942
  -4.750  -0.5669   0.02597   0.01965  -0.0241   0.9964   0.5517
  -4.500  -0.5331   0.02795   0.02158  -0.0236   0.9912   0.5740
  -4.250  -0.5059   0.02959   0.02317  -0.0220   0.9846   0.5897
  -4.000  -0.4796   0.03170   0.02529  -0.0190   0.9789   0.5981
  -3.750  -0.4501   0.03278   0.02630  -0.0190   0.9733   0.6135
  -3.500  -0.4306   0.03471   0.02825  -0.0144   0.9668   0.6186
  -3.250  -0.3931   0.03590   0.02936  -0.0156   0.9621   0.6342
  -3.000  -0.3831   0.03734   0.03084  -0.0097   0.9552   0.6389
  -2.750  -0.3489   0.03789   0.03130  -0.0115   0.9499   0.6547
  -2.500  -0.3266   0.03930   0.03273  -0.0075   0.9445   0.6596
  -2.250  -0.3006   0.03951   0.03289  -0.0086   0.9374   0.6751
  -2.000  -0.2791   0.04091   0.03433  -0.0036   0.9320   0.6816
  -1.750  -0.2533   0.04157   0.03496  -0.0035   0.9258   0.6988
  -1.500  -0.2390   0.04256   0.03600   0.0024   0.9189   0.7075
  -1.250  -0.2037   0.04289   0.03629   0.0009   0.9136   0.7230
  -1.000  -0.1852   0.04318   0.03659   0.0038   0.9066   0.7309
  -0.750  -0.1574   0.04298   0.03635   0.0012   0.8985   0.7429
  -0.500  -0.1185   0.04297   0.03635   0.0014   0.8937   0.7492
  -0.250  -0.1060   0.04286   0.03624   0.0032   0.8828   0.7577
   0.000  -0.0646   0.04252   0.03588   0.0005   0.8758   0.7665
   0.250  -0.0456   0.04237   0.03576   0.0023   0.8659   0.7730
   0.500  -0.0060   0.04194   0.03532  -0.0006   0.8571   0.7796
   0.750   0.0233   0.04155   0.03492  -0.0023   0.8463   0.7846
   1.000   0.0622   0.04083   0.03423  -0.0028   0.8371   0.7896
   1.250   0.0933   0.04032   0.03374  -0.0033   0.8255   0.7948
   1.500   0.1516   0.03910   0.03253  -0.0081   0.8155   0.7985
   1.750   0.1858   0.03841   0.03185  -0.0100   0.8013   0.8021
   2.000   0.2630   0.03619   0.02968  -0.0152   0.7949   0.8062
   2.250   0.2971   0.03513   0.02866  -0.0154   0.7818   0.8090
   2.500   0.3653   0.03314   0.02671  -0.0203   0.7743   0.8129
   2.750   0.3927   0.03227   0.02588  -0.0200   0.7598   0.8154
   3.000   0.4445   0.03064   0.02427  -0.0230   0.7469   0.8173
   3.250   0.4886   0.02923   0.02286  -0.0249   0.7297   0.8189
   3.500   0.5167   0.02837   0.02202  -0.0248   0.7074   0.8203
   3.750   0.5407   0.02745   0.02112  -0.0233   0.6817   0.8225
   4.000   0.5659   0.02653   0.02018  -0.0217   0.6495   0.8250
   4.250   0.5855   0.02592   0.01949  -0.0196   0.6033   0.8270
   4.500   0.6026   0.02555   0.01878  -0.0172   0.5232   0.8289
   4.750   0.6096   0.02603   0.01850  -0.0135   0.4156   0.8312
   5.000   0.6166   0.02697   0.01881  -0.0108   0.3435   0.8331
   5.250   0.6316   0.02781   0.01925  -0.0096   0.2966   0.8344
   5.500   0.6531   0.02861   0.01974  -0.0096   0.2654   0.8362
   5.750   0.6801   0.02943   0.02031  -0.0106   0.2423   0.8386
   6.000   0.7011   0.02986   0.02062  -0.0097   0.2266   0.8405
   6.250   0.7271   0.03046   0.02111  -0.0099   0.2130   0.8421
   6.500   0.7563   0.03119   0.02166  -0.0107   0.2019   0.8438
   6.750   0.7844   0.03179   0.02224  -0.0114   0.1920   0.8456
   7.000   0.8163   0.03266   0.02305  -0.0127   0.1836   0.8476
   7.250   0.8474   0.03343   0.02376  -0.0140   0.1758   0.8496
   7.500   0.8814   0.03451   0.02481  -0.0159   0.1690   0.8518
   7.750   0.9128   0.03544   0.02582  -0.0174   0.1626   0.8545
   8.000   0.9452   0.03659   0.02675  -0.0186   0.1572   0.8572
   8.250   0.9647   0.03729   0.02774  -0.0175   0.1527   0.8600
   8.500   0.9904   0.03821   0.02874  -0.0178   0.1480   0.8625
   8.750   1.0258   0.03974   0.03005  -0.0199   0.1435   0.8650
   9.000   1.0450   0.04088   0.03160  -0.0193   0.1399   0.8676
   9.250   1.0713   0.04228   0.03316  -0.0201   0.1360   0.8701
   9.500   1.0965   0.04339   0.03426  -0.0204   0.1327   0.8727
   9.750   1.1181   0.04509   0.03603  -0.0202   0.1298   0.8756
  10.000   1.1274   0.04672   0.03808  -0.0182   0.1273   0.8789
  10.250   1.1415   0.04859   0.04023  -0.0173   0.1248   0.8826
  10.500   1.1632   0.05037   0.04212  -0.0176   0.1223   0.8862
  10.750   1.1853   0.05169   0.04338  -0.0174   0.1200   0.8899
  11.000   1.1934   0.05422   0.04615  -0.0159   0.1182   0.8933
  11.250   1.1845   0.05691   0.04932  -0.0128   0.1169   0.8964
  11.500   1.1721   0.05985   0.05267  -0.0097   0.1159   0.8994
  11.750   1.1546   0.06306   0.05624  -0.0064   0.1152   0.9024
  12.000   1.1318   0.06691   0.06043  -0.0036   0.1149   0.9054
  12.250   1.1013   0.07176   0.06564  -0.0017   0.1149   0.9082
  12.500   1.0603   0.07815   0.07239  -0.0013   0.1154   0.9103
  12.750   1.0049   0.08712   0.08172  -0.0034   0.1165   0.9115
  13.000   0.9510   0.09810   0.09296  -0.0081   0.1179   0.9122
  13.250   0.9227   0.10769   0.10268  -0.0128   0.1188   0.9137
<< Back to NASA SC(2)-0518 AIRFOIL (sc20518-il)

Polar data table (+)

Polar graphs


<< Back to NASA SC(2)-0518 AIRFOIL (sc20518-il)