FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-158 AIRFOIL (fx63158-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.9 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63158-il-1000000-n5.txt Download as CSV file: xf-fx63158-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-158 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0636 0.07969 0.07582 -0.1076 0.4915 0.0077
-8.250 -0.2748 0.02530 0.01985 -0.1238 0.4915 0.0043
-8.000 -0.2642 0.02265 0.01686 -0.1225 0.4802 0.0042
-7.750 -0.2474 0.02064 0.01458 -0.1217 0.4758 0.0042
-7.500 -0.2281 0.01897 0.01265 -0.1209 0.4673 0.0042
-7.250 -0.2068 0.01782 0.01130 -0.1202 0.4590 0.0042
-7.000 -0.1854 0.01703 0.01028 -0.1195 0.4271 0.0042
-6.750 -0.1630 0.01630 0.00936 -0.1189 0.4107 0.0042
-6.500 -0.1396 0.01568 0.00860 -0.1185 0.3965 0.0042
-6.250 -0.1169 0.01526 0.00796 -0.1179 0.3584 0.0043
-6.000 -0.0926 0.01486 0.00742 -0.1177 0.3397 0.0043
-5.750 -0.0688 0.01462 0.00699 -0.1173 0.2976 0.0043
-5.250 -0.0192 0.01355 0.00552 -0.1176 0.2239 0.0048
-5.000 0.0077 0.01335 0.00516 -0.1179 0.1822 0.0050
-4.750 0.0362 0.01310 0.00484 -0.1184 0.1734 0.0052
-4.500 0.0653 0.01286 0.00455 -0.1190 0.1680 0.0055
-4.250 0.0944 0.01268 0.00431 -0.1196 0.1586 0.0058
-4.000 0.1231 0.01258 0.00410 -0.1201 0.1345 0.0060
-3.750 0.1524 0.01246 0.00391 -0.1206 0.1286 0.0062
-3.500 0.1819 0.01234 0.00375 -0.1212 0.1254 0.0064
-3.250 0.2114 0.01225 0.00362 -0.1218 0.1222 0.0065
-3.000 0.2407 0.01219 0.00351 -0.1223 0.1158 0.0068
-2.750 0.2703 0.01212 0.00340 -0.1228 0.1122 0.0076
-2.500 0.2990 0.01213 0.00334 -0.1232 0.0929 0.0080
-2.000 0.3574 0.01210 0.00327 -0.1241 0.0874 0.0095
-1.750 0.3864 0.01211 0.00325 -0.1245 0.0864 0.0141
-1.500 0.4153 0.01213 0.00324 -0.1249 0.0854 0.0157
-1.250 0.4441 0.01215 0.00324 -0.1252 0.0845 0.0175
-1.000 0.4731 0.01217 0.00325 -0.1256 0.0836 0.0209
-0.750 0.5018 0.01221 0.00329 -0.1260 0.0827 0.0330
-0.500 0.5302 0.01227 0.00333 -0.1263 0.0820 0.0349
-0.250 0.5588 0.01231 0.00336 -0.1266 0.0813 0.0378
0.000 0.5873 0.01236 0.00339 -0.1269 0.0808 0.0412
0.250 0.6157 0.01243 0.00345 -0.1272 0.0803 0.0426
0.500 0.6439 0.01249 0.00351 -0.1274 0.0800 0.0441
0.750 0.6723 0.01256 0.00357 -0.1277 0.0798 0.0461
1.000 0.7020 0.01255 0.00365 -0.1284 0.0797 0.0988
1.250 0.7304 0.01260 0.00373 -0.1287 0.0795 0.1130
1.500 0.7589 0.01266 0.00382 -0.1291 0.0790 0.1369
1.750 0.7868 0.01275 0.00392 -0.1293 0.0786 0.1429
2.000 0.8147 0.01284 0.00402 -0.1295 0.0781 0.1511
2.250 0.8434 0.01290 0.00413 -0.1300 0.0774 0.1760
2.500 0.8712 0.01299 0.00424 -0.1302 0.0740 0.1966
2.750 0.8989 0.01314 0.00441 -0.1306 0.0601 0.2411
3.250 0.9583 0.01319 0.00472 -0.1322 0.0568 0.3673
3.500 0.9935 0.01299 0.00488 -0.1346 0.0563 0.5142
3.750 1.0231 0.01304 0.00513 -0.1353 0.0558 0.5886
4.000 1.0494 0.01324 0.00538 -0.1353 0.0554 0.6152
4.250 1.0751 0.01345 0.00562 -0.1350 0.0549 0.6281
4.500 1.1004 0.01368 0.00586 -0.1348 0.0545 0.6343
4.750 1.1254 0.01391 0.00609 -0.1344 0.0541 0.6363
5.000 1.1503 0.01415 0.00635 -0.1341 0.0537 0.6400
5.250 1.1748 0.01440 0.00664 -0.1337 0.0533 0.6447
5.500 1.1988 0.01466 0.00692 -0.1332 0.0527 0.6485
5.750 1.2222 0.01496 0.00723 -0.1326 0.0517 0.6514
6.000 1.2452 0.01526 0.00754 -0.1319 0.0509 0.6533
6.250 1.2686 0.01552 0.00782 -0.1313 0.0508 0.6546
6.500 1.2916 0.01579 0.00812 -0.1307 0.0506 0.6559
6.750 1.3143 0.01605 0.00842 -0.1300 0.0501 0.6574
7.000 1.3366 0.01632 0.00872 -0.1293 0.0490 0.6590
7.250 1.3573 0.01660 0.00904 -0.1282 0.0475 0.6605
7.500 1.3761 0.01691 0.00938 -0.1268 0.0461 0.6620
7.750 1.3939 0.01728 0.00977 -0.1252 0.0444 0.6635
8.000 1.4122 0.01762 0.01014 -0.1238 0.0434 0.6650
8.250 1.4310 0.01795 0.01050 -0.1225 0.0418 0.6666
8.750 1.4589 0.01906 0.01154 -0.1184 0.0272 0.6696
9.000 1.4711 0.01972 0.01220 -0.1162 0.0241 0.6710
9.250 1.4855 0.02029 0.01282 -0.1144 0.0226 0.6727
9.500 1.4972 0.02101 0.01357 -0.1123 0.0191 0.6745
9.750 1.5030 0.02206 0.01462 -0.1095 0.0139 0.6765
10.000 1.5119 0.02300 0.01559 -0.1073 0.0120 0.6787
10.250 1.5200 0.02405 0.01668 -0.1051 0.0104 0.6811
10.500 1.5291 0.02509 0.01777 -0.1033 0.0094 0.6836
10.750 1.5343 0.02645 0.01917 -0.1012 0.0068 0.6858
11.000 1.5324 0.02845 0.02119 -0.0987 0.0024 0.6874
11.250 1.5379 0.03004 0.02286 -0.0971 0.0022 0.6896
11.500 1.5433 0.03176 0.02466 -0.0958 0.0020 0.6920
11.750 1.5480 0.03363 0.02662 -0.0946 0.0019 0.6937
12.000 1.5524 0.03564 0.02872 -0.0936 0.0018 0.6957
12.250 1.5565 0.03778 0.03094 -0.0928 0.0017 0.6975
12.500 1.5601 0.04005 0.03329 -0.0921 0.0016 0.6992
12.750 1.5634 0.04243 0.03575 -0.0915 0.0015 0.7008
13.000 1.5668 0.04487 0.03828 -0.0911 0.0015 0.7024
13.250 1.5697 0.04744 0.04092 -0.0908 0.0015 0.7037
13.500 1.5719 0.05013 0.04370 -0.0905 0.0014 0.7049
13.750 1.5737 0.05295 0.04661 -0.0904 0.0014 0.7065
14.000 1.5751 0.05590 0.04965 -0.0904 0.0014 0.7079
14.250 1.5763 0.05892 0.05277 -0.0905 0.0013 0.7092
14.500 1.5771 0.06207 0.05601 -0.0906 0.0013 0.7104
14.750 1.5776 0.06533 0.05937 -0.0909 0.0012 0.7115
15.000 1.5776 0.06876 0.06288 -0.0913 0.0012 0.7127
15.250 1.5776 0.07223 0.06645 -0.0918 0.0011 0.7138
15.500 1.5777 0.07575 0.07006 -0.0924 0.0011 0.7150
15.750 1.5768 0.07951 0.07391 -0.0931 0.0011 0.7161
16.000 1.5755 0.08339 0.07790 -0.0940 0.0010 0.7173
16.250 1.5750 0.08721 0.08180 -0.0949 0.0010 0.7184
16.500 1.5724 0.09140 0.08610 -0.0960 0.0010 0.7195
16.750 1.5703 0.09558 0.09037 -0.0971 0.0009 0.7205
17.000 1.5681 0.09982 0.09471 -0.0984 0.0009 0.7215
17.500 1.5608 0.10901 0.10411 -0.1015 0.0009 0.7237
17.750 1.5560 0.11384 0.10906 -0.1032 0.0008 0.7249
18.000 1.5510 0.11880 0.11412 -0.1052 0.0008 0.7262
18.250 1.5460 0.12377 0.11922 -0.1072 0.0008 0.7275
18.500 1.5389 0.12918 0.12474 -0.1096 0.0008 0.7288
18.750 1.5339 0.13421 0.12988 -0.1120 0.0008 0.7302
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