NASA SC(2)-0518 AIRFOIL (sc20518-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0518 AIRFOIL (sc20518-il) Reynolds number: 50,000 Max Cl/Cd: 20.86 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20518-il-50000-n5.txt Download as CSV file: xf-sc20518-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6513 0.09846 0.08872 -0.0558 1.0000 0.1149
-13.250 -0.7543 0.08048 0.07034 -0.0648 1.0000 0.1148
-13.000 -0.8035 0.07259 0.06215 -0.0670 1.0000 0.1151
-12.750 -0.8389 0.06713 0.05640 -0.0673 1.0000 0.1158
-12.500 -0.8427 0.06438 0.05357 -0.0666 1.0000 0.1172
-12.250 -0.8354 0.06256 0.05177 -0.0658 1.0000 0.1191
-12.000 -0.8382 0.06025 0.04938 -0.0646 1.0000 0.1209
-11.750 -0.8449 0.05787 0.04687 -0.0631 1.0000 0.1226
-11.500 -0.8529 0.05561 0.04445 -0.0610 1.0000 0.1244
-11.250 -0.8619 0.05352 0.04218 -0.0585 1.0000 0.1261
-11.000 -0.8735 0.05165 0.04008 -0.0553 1.0000 0.1277
-10.750 -0.8523 0.05061 0.03917 -0.0544 1.0000 0.1303
-10.500 -0.8430 0.04948 0.03805 -0.0525 1.0000 0.1330
-10.250 -0.8380 0.04823 0.03673 -0.0502 1.0000 0.1358
-10.000 -0.8332 0.04690 0.03525 -0.0480 1.0000 0.1386
-9.750 -0.8190 0.04586 0.03419 -0.0462 1.0000 0.1416
-9.500 -0.8018 0.04514 0.03355 -0.0445 1.0000 0.1451
-9.250 -0.7900 0.04431 0.03269 -0.0425 1.0000 0.1490
-9.000 -0.7797 0.04343 0.03168 -0.0403 1.0000 0.1532
-8.750 -0.7601 0.04293 0.03133 -0.0385 1.0000 0.1574
-8.500 -0.7471 0.04234 0.03075 -0.0363 1.0000 0.1621
-8.250 -0.7371 0.04168 0.02999 -0.0339 1.0000 0.1675
-8.000 -0.7255 0.04116 0.02964 -0.0315 1.0000 0.1726
-7.750 -0.7172 0.04057 0.02910 -0.0289 1.0000 0.1786
-7.500 -0.7092 0.03996 0.02854 -0.0264 1.0000 0.1849
-7.250 -0.7033 0.03931 0.02800 -0.0237 1.0000 0.1918
-7.000 -0.6969 0.03864 0.02738 -0.0212 1.0000 0.2002
-6.750 -0.6918 0.03788 0.02676 -0.0188 1.0000 0.2093
-6.500 -0.6860 0.03706 0.02607 -0.0166 1.0000 0.2204
-6.250 -0.6796 0.03616 0.02531 -0.0148 1.0000 0.2346
-6.000 -0.6722 0.03515 0.02450 -0.0133 1.0000 0.2525
-5.750 -0.6492 0.03392 0.02361 -0.0149 0.9953 0.2859
-5.500 -0.6233 0.03305 0.02331 -0.0163 0.9902 0.3369
-5.250 -0.5974 0.03393 0.02483 -0.0141 0.9846 0.3979
-5.000 -0.5642 0.03620 0.02740 -0.0114 0.9797 0.4474
-4.750 -0.5324 0.03740 0.02857 -0.0112 0.9741 0.4856
-4.500 -0.5035 0.03758 0.02860 -0.0127 0.9677 0.5199
-4.250 -0.4692 0.03810 0.02897 -0.0146 0.9626 0.5464
-4.000 -0.4440 0.03876 0.02954 -0.0140 0.9556 0.5641
-3.750 -0.4131 0.03954 0.03022 -0.0141 0.9498 0.5806
-3.500 -0.3833 0.04029 0.03088 -0.0141 0.9443 0.5975
-3.250 -0.3597 0.04094 0.03148 -0.0131 0.9372 0.6146
-3.000 -0.3294 0.04189 0.03238 -0.0126 0.9319 0.6309
-2.750 -0.3023 0.04302 0.03349 -0.0102 0.9268 0.6413
-2.500 -0.2812 0.04306 0.03347 -0.0099 0.9193 0.6557
-2.000 -0.2263 0.04321 0.03350 -0.0105 0.9081 0.6758
-1.750 -0.2045 0.04348 0.03378 -0.0086 0.9013 0.6811
-1.500 -0.1748 0.04352 0.03378 -0.0090 0.8960 0.6890
-1.250 -0.1489 0.04322 0.03342 -0.0104 0.8899 0.6989
-1.000 -0.1296 0.04328 0.03349 -0.0087 0.8821 0.7038
-0.750 -0.0988 0.04316 0.03335 -0.0095 0.8764 0.7098
-0.500 -0.0730 0.04290 0.03306 -0.0107 0.8695 0.7169
-0.250 -0.0522 0.04273 0.03289 -0.0105 0.8610 0.7224
0.000 -0.0191 0.04258 0.03274 -0.0114 0.8554 0.7264
0.250 0.0006 0.04249 0.03267 -0.0107 0.8464 0.7310
0.500 0.0302 0.04224 0.03244 -0.0119 0.8381 0.7358
0.750 0.0699 0.04187 0.03205 -0.0151 0.8313 0.7410
1.000 0.0889 0.04170 0.03193 -0.0142 0.8192 0.7445
1.250 0.1323 0.04121 0.03148 -0.0164 0.8127 0.7473
1.500 0.1488 0.04107 0.03138 -0.0150 0.7986 0.7503
1.750 0.1898 0.04048 0.03084 -0.0170 0.7895 0.7534
2.000 0.2186 0.04005 0.03047 -0.0174 0.7758 0.7572
2.250 0.2511 0.03949 0.02995 -0.0184 0.7611 0.7610
2.500 0.2994 0.03833 0.02885 -0.0209 0.7482 0.7640
2.750 0.3344 0.03737 0.02796 -0.0207 0.7324 0.7666
3.000 0.3614 0.03665 0.02731 -0.0196 0.7142 0.7694
3.250 0.3921 0.03580 0.02653 -0.0192 0.6950 0.7722
3.500 0.4245 0.03487 0.02566 -0.0189 0.6735 0.7751
3.750 0.4458 0.03438 0.02524 -0.0176 0.6469 0.7785
4.000 0.4769 0.03367 0.02456 -0.0177 0.6174 0.7817
4.250 0.4997 0.03323 0.02415 -0.0166 0.5811 0.7843
4.500 0.5222 0.03273 0.02360 -0.0148 0.5360 0.7864
4.750 0.5522 0.03220 0.02273 -0.0139 0.4706 0.7885
5.000 0.5734 0.03235 0.02237 -0.0124 0.4039 0.7909
5.250 0.5873 0.03301 0.02262 -0.0106 0.3532 0.7938
5.500 0.6017 0.03382 0.02313 -0.0093 0.3142 0.7971
5.750 0.6195 0.03470 0.02378 -0.0088 0.2837 0.8004
6.000 0.6386 0.03557 0.02446 -0.0085 0.2597 0.8033
6.250 0.6555 0.03629 0.02507 -0.0073 0.2414 0.8057
6.500 0.6759 0.03702 0.02571 -0.0068 0.2258 0.8081
6.750 0.6990 0.03777 0.02639 -0.0067 0.2121 0.8107
7.000 0.7248 0.03854 0.02707 -0.0070 0.2007 0.8134
7.250 0.7527 0.03932 0.02780 -0.0077 0.1902 0.8164
7.500 0.7851 0.04015 0.02865 -0.0091 0.1805 0.8197
7.750 0.8142 0.04092 0.02930 -0.0096 0.1730 0.8228
8.000 0.8403 0.04173 0.03025 -0.0096 0.1656 0.8259
8.250 0.8689 0.04259 0.03107 -0.0101 0.1593 0.8292
8.500 0.8986 0.04368 0.03224 -0.0110 0.1534 0.8325
8.750 0.9263 0.04482 0.03346 -0.0118 0.1477 0.8357
9.000 0.9599 0.04602 0.03454 -0.0135 0.1431 0.8388
9.250 0.9765 0.04730 0.03613 -0.0125 0.1387 0.8418
9.500 0.9960 0.04852 0.03748 -0.0120 0.1346 0.8455
9.750 1.0222 0.04971 0.03859 -0.0125 0.1312 0.8495
10.000 1.0373 0.05154 0.04072 -0.0120 0.1279 0.8536
10.250 1.0483 0.05323 0.04265 -0.0108 0.1247 0.8574
10.500 1.0623 0.05469 0.04423 -0.0098 0.1218 0.8615
10.750 1.0847 0.05607 0.04556 -0.0101 0.1193 0.8657
11.000 1.0872 0.05870 0.04855 -0.0089 0.1170 0.8696
11.250 1.0843 0.06142 0.05163 -0.0073 0.1149 0.8731
11.500 1.0824 0.06400 0.05448 -0.0059 0.1129 0.8768
11.750 1.0834 0.06657 0.05724 -0.0051 0.1110 0.8810
12.000 1.0911 0.06892 0.05969 -0.0050 0.1093 0.8855
12.250 1.0950 0.07128 0.06214 -0.0042 0.1079 0.8900
12.500 1.0639 0.07658 0.06789 -0.0036 0.1072 0.8935
12.750 1.0247 0.08347 0.07521 -0.0047 0.1068 0.8963
13.000 0.9684 0.09366 0.08583 -0.0087 0.1067 0.8976
13.250 0.8383 0.12087 0.11360 -0.0257 0.1071 0.8926
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0518 AIRFOIL (sc20518-il)