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

SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.67 at α=-0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nasasc2-0714-il-1000000.txt
Download as CSV file: xf-nasasc2-0714-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SC(2)-0714 Supercritical airfoil (coordinates fr
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.1778   0.08108   0.07746  -0.0649   1.0000   0.0235
 -19.500  -1.1876   0.07605   0.07233  -0.0674   1.0000   0.0236
 -19.250  -1.1956   0.07137   0.06755  -0.0698   1.0000   0.0238
 -19.000  -1.2013   0.06716   0.06326  -0.0717   1.0000   0.0239
 -18.750  -1.2053   0.06332   0.05933  -0.0734   1.0000   0.0241
 -18.500  -1.2077   0.05980   0.05572  -0.0749   1.0000   0.0243
 -18.250  -1.2088   0.05656   0.05240  -0.0761   1.0000   0.0245
 -18.000  -1.2087   0.05360   0.04936  -0.0770   1.0000   0.0247
 -17.750  -1.2075   0.05089   0.04657  -0.0777   1.0000   0.0249
 -17.500  -1.2051   0.04846   0.04406  -0.0782   1.0000   0.0251
 -17.250  -1.2022   0.04621   0.04174  -0.0784   1.0000   0.0253
 -17.000  -1.1988   0.04413   0.03959  -0.0783   1.0000   0.0255
 -16.750  -1.1946   0.04229   0.03767  -0.0780   1.0000   0.0257
 -16.500  -1.1898   0.04061   0.03592  -0.0775   1.0000   0.0259
 -16.250  -1.1848   0.03907   0.03432  -0.0768   1.0000   0.0261
 -16.000  -1.1877   0.03708   0.03227  -0.0755   1.0000   0.0264
 -15.750  -1.1920   0.03525   0.03038  -0.0737   1.0000   0.0268
 -15.500  -1.1937   0.03384   0.02894  -0.0716   1.0000   0.0272
 -15.250  -1.1940   0.03267   0.02775  -0.0693   1.0000   0.0275
 -15.000  -1.1944   0.03161   0.02666  -0.0669   1.0000   0.0277
 -14.750  -1.1939   0.03067   0.02569  -0.0642   1.0000   0.0280
 -14.500  -1.1947   0.02976   0.02475  -0.0614   1.0000   0.0283
 -14.250  -1.1880   0.02884   0.02379  -0.0598   0.9996   0.0287
 -14.000  -1.1671   0.02782   0.02272  -0.0609   0.9985   0.0292
 -13.750  -1.1455   0.02685   0.02171  -0.0620   0.9971   0.0297
 -13.500  -1.1223   0.02602   0.02082  -0.0632   0.9958   0.0301
 -13.250  -1.0983   0.02526   0.02000  -0.0643   0.9945   0.0305
 -13.000  -1.0797   0.02394   0.01864  -0.0655   0.9931   0.0312
 -12.750  -1.0625   0.02293   0.01761  -0.0657   0.9904   0.0319
 -12.500  -1.0380   0.02215   0.01682  -0.0669   0.9882   0.0326
 -12.250  -1.0104   0.02147   0.01613  -0.0683   0.9865   0.0333
 -12.000  -0.9815   0.02082   0.01545  -0.0700   0.9852   0.0340
 -11.750  -0.9516   0.02021   0.01482  -0.0718   0.9841   0.0347
 -11.500  -0.9208   0.01969   0.01426  -0.0736   0.9833   0.0353
 -11.250  -0.8905   0.01885   0.01339  -0.0758   0.9825   0.0362
 -11.000  -0.8590   0.01808   0.01262  -0.0782   0.9819   0.0374
 -10.750  -0.8262   0.01757   0.01212  -0.0804   0.9814   0.0385
 -10.500  -0.8033   0.01712   0.01166  -0.0804   0.9783   0.0394
 -10.250  -0.7748   0.01668   0.01120  -0.0816   0.9763   0.0403
 -10.000  -0.7435   0.01629   0.01078  -0.0831   0.9749   0.0410
  -9.750  -0.7107   0.01556   0.01003  -0.0855   0.9738   0.0425
  -9.500  -0.6768   0.01501   0.00951  -0.0878   0.9729   0.0441
  -9.250  -0.6425   0.01459   0.00908  -0.0900   0.9722   0.0454
  -9.000  -0.6079   0.01419   0.00868  -0.0922   0.9717   0.0467
  -8.750  -0.5730   0.01387   0.00834  -0.0942   0.9712   0.0476
  -8.500  -0.5365   0.01326   0.00774  -0.0972   0.9708   0.0502
  -8.250  -0.5004   0.01285   0.00736  -0.0996   0.9704   0.0522
  -8.000  -0.4645   0.01252   0.00702  -0.1019   0.9701   0.0540
  -7.750  -0.4284   0.01216   0.00665  -0.1043   0.9696   0.0560
  -7.500  -0.3917   0.01174   0.00628  -0.1068   0.9692   0.0598
  -7.250  -0.3556   0.01144   0.00599  -0.1091   0.9687   0.0629
  -7.000  -0.3190   0.01107   0.00566  -0.1115   0.9682   0.0686
  -6.750  -0.2892   0.01082   0.00545  -0.1123   0.9659   0.0743
  -6.500  -0.2576   0.01053   0.00522  -0.1136   0.9637   0.0833
  -6.250  -0.2234   0.01022   0.00498  -0.1154   0.9621   0.0949
  -6.000  -0.1885   0.00992   0.00475  -0.1173   0.9609   0.1068
  -5.750  -0.1534   0.00963   0.00452  -0.1192   0.9597   0.1201
  -5.500  -0.1176   0.00931   0.00429  -0.1213   0.9586   0.1391
  -5.250  -0.0798   0.00888   0.00403  -0.1240   0.9578   0.1747
  -5.000  -0.0402   0.00835   0.00374  -0.1273   0.9569   0.2297
  -4.750   0.0025   0.00766   0.00339  -0.1315   0.9563   0.3146
  -4.500   0.0490   0.00678   0.00299  -0.1367   0.9561   0.4414
  -4.250   0.0891   0.00631   0.00282  -0.1399   0.9552   0.5287
  -4.000   0.1220   0.00622   0.00280  -0.1409   0.9530   0.5607
  -3.750   0.1507   0.00616   0.00277  -0.1409   0.9486   0.5764
  -3.500   0.1811   0.00610   0.00272  -0.1412   0.9446   0.5879
  -3.250   0.2121   0.00606   0.00265  -0.1416   0.9411   0.5988
  -3.000   0.2419   0.00604   0.00266  -0.1416   0.9368   0.6068
  -2.750   0.2702   0.00599   0.00260  -0.1414   0.9295   0.6127
  -2.500   0.2994   0.00591   0.00247  -0.1412   0.9205   0.6173
  -2.250   0.3275   0.00586   0.00243  -0.1409   0.9101   0.6216
  -2.000   0.3564   0.00591   0.00246  -0.1407   0.9006   0.6275
  -1.750   0.3860   0.00598   0.00247  -0.1407   0.8900   0.6326
  -1.500   0.4143   0.00600   0.00254  -0.1405   0.8792   0.6383
  -1.250   0.4430   0.00609   0.00261  -0.1403   0.8684   0.6425
  -1.000   0.4721   0.00613   0.00261  -0.1403   0.8526   0.6448
  -0.750   0.5011   0.00618   0.00259  -0.1403   0.8320   0.6463
  -0.500   0.5288   0.00632   0.00258  -0.1399   0.7970   0.6480
  -0.250   0.5539   0.00666   0.00264  -0.1391   0.7340   0.6498
   0.000   0.5747   0.00730   0.00279  -0.1375   0.6254   0.6521
   0.250   0.5949   0.00812   0.00307  -0.1359   0.5009   0.6538
   0.500   0.6172   0.00883   0.00333  -0.1349   0.3987   0.6553
   0.750   0.6406   0.00946   0.00357  -0.1340   0.3086   0.6567
   1.000   0.6652   0.00999   0.00380  -0.1334   0.2403   0.6582
   1.250   0.6909   0.01042   0.00400  -0.1330   0.1906   0.6596
   1.500   0.7171   0.01081   0.00419  -0.1326   0.1537   0.6611
   1.750   0.7440   0.01110   0.00437  -0.1324   0.1296   0.6626
   2.000   0.7710   0.01140   0.00455  -0.1321   0.1108   0.6639
   2.250   0.7981   0.01168   0.00473  -0.1319   0.0953   0.6651
   2.500   0.8253   0.01194   0.00492  -0.1317   0.0831   0.6662
   2.750   0.8527   0.01218   0.00509  -0.1315   0.0761   0.6672
   3.000   0.8800   0.01241   0.00528  -0.1313   0.0706   0.6683
   3.250   0.9073   0.01259   0.00546  -0.1311   0.0673   0.6700
   3.500   0.9339   0.01286   0.00570  -0.1307   0.0635   0.6714
   3.750   0.9608   0.01309   0.00593  -0.1304   0.0613   0.6727
   4.000   0.9877   0.01330   0.00616  -0.1301   0.0595   0.6740
   4.250   1.0140   0.01357   0.00642  -0.1296   0.0573   0.6754
   4.500   1.0393   0.01396   0.00679  -0.1290   0.0543   0.6770
   4.750   1.0658   0.01418   0.00704  -0.1286   0.0530   0.6788
   5.000   1.0923   0.01441   0.00728  -0.1282   0.0514   0.6805
   5.250   1.1183   0.01468   0.00754  -0.1278   0.0497   0.6820
   5.500   1.1433   0.01506   0.00790  -0.1271   0.0476   0.6832
   5.750   1.1684   0.01542   0.00827  -0.1265   0.0461   0.6844
   6.000   1.1944   0.01565   0.00851  -0.1260   0.0450   0.6854
   6.250   1.2202   0.01587   0.00875  -0.1255   0.0436   0.6875
   6.500   1.2452   0.01615   0.00903  -0.1249   0.0421   0.6891
   6.750   1.2679   0.01668   0.00956  -0.1238   0.0403   0.6906
   7.000   1.2929   0.01693   0.00984  -0.1231   0.0396   0.6920
   7.250   1.3174   0.01722   0.01017  -0.1224   0.0387   0.6934
   7.500   1.3415   0.01754   0.01050  -0.1215   0.0377   0.6949
   7.750   1.3650   0.01789   0.01086  -0.1206   0.0367   0.6964
   8.000   1.3874   0.01834   0.01131  -0.1195   0.0356   0.6979
   8.250   1.4077   0.01895   0.01194  -0.1181   0.0346   0.6994
   8.500   1.4308   0.01927   0.01230  -0.1171   0.0340   0.7008
   8.750   1.4529   0.01965   0.01270  -0.1160   0.0333   0.7020
   9.000   1.4743   0.02005   0.01314  -0.1147   0.0326   0.7033
   9.250   1.4949   0.02046   0.01358  -0.1133   0.0320   0.7052
   9.500   1.5142   0.02092   0.01408  -0.1117   0.0314   0.7069
   9.750   1.5314   0.02150   0.01468  -0.1097   0.0307   0.7084
  10.000   1.5418   0.02231   0.01554  -0.1065   0.0300   0.7100
  10.250   1.5564   0.02295   0.01625  -0.1041   0.0296   0.7116
  10.500   1.5737   0.02347   0.01683  -0.1022   0.0293   0.7133
  10.750   1.5907   0.02403   0.01745  -0.1003   0.0289   0.7150
  11.000   1.6067   0.02467   0.01814  -0.0983   0.0286   0.7167
  11.250   1.6224   0.02532   0.01885  -0.0963   0.0282   0.7183
  11.500   1.6372   0.02603   0.01960  -0.0942   0.0278   0.7197
  11.750   1.6520   0.02674   0.02037  -0.0922   0.0274   0.7217
  12.000   1.6657   0.02751   0.02120  -0.0900   0.0270   0.7238
  12.250   1.6784   0.02836   0.02212  -0.0878   0.0267   0.7256
  12.500   1.6894   0.02935   0.02316  -0.0854   0.0263   0.7274
  12.750   1.6968   0.03060   0.02448  -0.0827   0.0259   0.7292
  13.000   1.6971   0.03245   0.02642  -0.0792   0.0254   0.7309
  13.250   1.7080   0.03349   0.02755  -0.0771   0.0253   0.7328
  13.500   1.7187   0.03455   0.02869  -0.0751   0.0251   0.7346
  13.750   1.7280   0.03575   0.02998  -0.0730   0.0249   0.7362
  14.000   1.7362   0.03708   0.03139  -0.0710   0.0247   0.7376
  14.250   1.7432   0.03851   0.03292  -0.0689   0.0245   0.7400
  14.500   1.7489   0.04008   0.03460  -0.0669   0.0243   0.7419
  14.750   1.7534   0.04180   0.03641  -0.0649   0.0241   0.7438
  15.000   1.7574   0.04363   0.03834  -0.0630   0.0239   0.7457
  15.250   1.7600   0.04564   0.04045  -0.0613   0.0237   0.7477
  15.500   1.7610   0.04786   0.04277  -0.0597   0.0236   0.7497
  15.750   1.7615   0.05023   0.04524  -0.0583   0.0234   0.7516
  16.000   1.7610   0.05284   0.04794  -0.0571   0.0232   0.7533
  16.250   1.7592   0.05573   0.05093  -0.0562   0.0231   0.7546
  16.500   1.7562   0.05890   0.05420  -0.0557   0.0230   0.7567
  16.750   1.7513   0.06246   0.05789  -0.0555   0.0228   0.7585
  17.000   1.7451   0.06640   0.06195  -0.0557   0.0227   0.7602
  17.250   1.7366   0.07088   0.06654  -0.0564   0.0226   0.7619
  17.500   1.7259   0.07589   0.07168  -0.0576   0.0225   0.7635
  17.750   1.7128   0.08150   0.07742  -0.0595   0.0224   0.7650
  18.000   1.6966   0.08787   0.08394  -0.0620   0.0223   0.7664
  18.250   1.6779   0.09489   0.09111  -0.0652   0.0223   0.7676
  18.500   1.6566   0.10258   0.09894  -0.0690   0.0222   0.7687
  18.750   1.6326   0.11090   0.10741  -0.0735   0.0221   0.7695
  19.000   1.6078   0.11958   0.11625  -0.0784   0.0221   0.7702
  19.250   1.5817   0.12873   0.12555  -0.0840   0.0220   0.7709
<< Back to SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)

Polar data table (+)

Polar graphs


<< Back to SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)