GOE 626 AIRFOIL (goe626-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 626 AIRFOIL (goe626-il) Reynolds number: 100,000 Max Cl/Cd: 51.59 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe626-il-100000-n5.txt Download as CSV file: xf-goe626-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 626 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4087 0.10621 0.10035 -0.0549 1.0000 0.0561
-12.500 -0.5244 0.08243 0.07626 -0.0660 1.0000 0.0568
-12.250 -0.5445 0.07750 0.07126 -0.0671 1.0000 0.0571
-12.000 -0.5601 0.07372 0.06742 -0.0673 1.0000 0.0577
-11.750 -0.5738 0.07066 0.06432 -0.0668 1.0000 0.0582
-11.500 -0.5871 0.06804 0.06167 -0.0658 1.0000 0.0587
-11.250 -0.5998 0.06579 0.05940 -0.0645 1.0000 0.0591
-11.000 -0.6136 0.06369 0.05728 -0.0628 1.0000 0.0596
-10.750 -0.6271 0.06189 0.05550 -0.0607 1.0000 0.0600
-10.500 -0.6258 0.05996 0.05361 -0.0613 0.9975 0.0608
-10.250 -0.6100 0.05748 0.05111 -0.0651 0.9912 0.0622
-10.000 -0.5988 0.05489 0.04849 -0.0686 0.9834 0.0638
-9.750 -0.5903 0.05229 0.04583 -0.0717 0.9756 0.0654
-9.500 -0.5750 0.04927 0.04277 -0.0764 0.9685 0.0678
-9.250 -0.5644 0.04607 0.03956 -0.0807 0.9596 0.0704
-9.000 -0.5420 0.04249 0.03588 -0.0873 0.9535 0.0753
-8.750 -0.5288 0.03872 0.03205 -0.0925 0.9442 0.0802
-8.500 -0.4999 0.03444 0.02765 -0.1007 0.9387 0.0889
-8.250 -0.4779 0.03129 0.02439 -0.1052 0.9308 0.0988
-8.000 -0.4473 0.02890 0.02190 -0.1096 0.9250 0.1125
-7.750 -0.4104 0.02720 0.02013 -0.1138 0.9213 0.1287
-7.500 -0.3871 0.02626 0.01919 -0.1144 0.9127 0.1429
-7.250 -0.3523 0.02570 0.01868 -0.1164 0.9074 0.1611
-7.000 -0.3121 0.02541 0.01838 -0.1189 0.9039 0.1790
-6.750 -0.2877 0.02549 0.01848 -0.1181 0.8945 0.1893
-6.500 -0.2503 0.02541 0.01831 -0.1196 0.8892 0.2010
-6.250 -0.2082 0.02511 0.01785 -0.1222 0.8856 0.2126
-6.000 -0.1840 0.02500 0.01760 -0.1215 0.8747 0.2212
-5.750 -0.1436 0.02512 0.01766 -0.1232 0.8693 0.2295
-5.500 -0.1130 0.02459 0.01686 -0.1241 0.8602 0.2398
-5.250 -0.0783 0.02517 0.01753 -0.1242 0.8522 0.2450
-5.000 -0.0431 0.02461 0.01667 -0.1259 0.8445 0.2554
-4.750 -0.0140 0.02491 0.01705 -0.1252 0.8340 0.2590
-4.500 0.0208 0.02479 0.01686 -0.1260 0.8258 0.2648
-4.250 0.0502 0.02423 0.01606 -0.1266 0.8143 0.2725
-4.000 0.0805 0.02438 0.01626 -0.1262 0.8036 0.2765
-3.750 0.1135 0.02422 0.01602 -0.1268 0.7930 0.2827
-3.500 0.1416 0.02364 0.01518 -0.1272 0.7796 0.2894
-3.250 0.1730 0.02341 0.01495 -0.1274 0.7681 0.2922
-3.000 0.2039 0.02312 0.01457 -0.1276 0.7554 0.2957
-2.750 0.2320 0.02278 0.01411 -0.1276 0.7411 0.2995
-2.500 0.2625 0.02230 0.01342 -0.1281 0.7278 0.3038
-2.250 0.2943 0.02185 0.01274 -0.1288 0.7150 0.3075
-2.000 0.3236 0.02161 0.01244 -0.1288 0.7014 0.3100
-1.750 0.3524 0.02139 0.01214 -0.1288 0.6882 0.3125
-1.500 0.3825 0.02117 0.01179 -0.1290 0.6760 0.3155
-1.250 0.4126 0.02097 0.01142 -0.1292 0.6641 0.3190
-1.000 0.4410 0.02080 0.01107 -0.1293 0.6521 0.3225
-0.750 0.4715 0.02063 0.01065 -0.1297 0.6416 0.3253
-0.500 0.4983 0.02052 0.01051 -0.1293 0.6303 0.3274
-0.250 0.5267 0.02048 0.01040 -0.1292 0.6203 0.3298
0.000 0.5536 0.02046 0.01034 -0.1289 0.6100 0.3326
0.250 0.5818 0.02046 0.01023 -0.1289 0.6008 0.3355
0.500 0.6083 0.02045 0.01015 -0.1285 0.5908 0.3382
0.750 0.6365 0.02046 0.01003 -0.1284 0.5820 0.3409
1.000 0.6622 0.02050 0.00999 -0.1280 0.5722 0.3437
1.250 0.6904 0.02052 0.00994 -0.1279 0.5644 0.3464
1.500 0.7146 0.02057 0.01007 -0.1271 0.5552 0.3490
1.750 0.7414 0.02063 0.01010 -0.1268 0.5473 0.3518
2.000 0.7668 0.02072 0.01018 -0.1262 0.5388 0.3545
2.250 0.7924 0.02080 0.01024 -0.1257 0.5306 0.3574
2.500 0.8190 0.02090 0.01028 -0.1253 0.5234 0.3604
2.750 0.8436 0.02103 0.01040 -0.1246 0.5148 0.3635
3.000 0.8697 0.02111 0.01045 -0.1242 0.5075 0.3667
3.250 0.8924 0.02123 0.01067 -0.1231 0.4982 0.3700
3.500 0.9172 0.02134 0.01074 -0.1224 0.4902 0.3738
3.750 0.9404 0.02151 0.01094 -0.1215 0.4818 0.3776
4.000 0.9646 0.02166 0.01108 -0.1207 0.4744 0.3813
4.250 0.9896 0.02184 0.01125 -0.1201 0.4682 0.3849
4.500 1.0121 0.02203 0.01154 -0.1191 0.4607 0.3886
4.750 1.0367 0.02221 0.01171 -0.1184 0.4539 0.3933
5.000 1.0595 0.02245 0.01199 -0.1174 0.4465 0.3989
5.250 1.0826 0.02269 0.01227 -0.1165 0.4396 0.4046
5.500 1.1072 0.02290 0.01247 -0.1158 0.4333 0.4110
5.750 1.1272 0.02318 0.01287 -0.1145 0.4251 0.4181
6.000 1.1497 0.02341 0.01312 -0.1134 0.4179 0.4256
6.250 1.1712 0.02370 0.01350 -0.1123 0.4113 0.4343
6.500 1.1920 0.02401 0.01391 -0.1111 0.4046 0.4445
6.750 1.2146 0.02427 0.01420 -0.1102 0.3985 0.4586
7.000 1.2332 0.02459 0.01470 -0.1087 0.3912 0.4767
7.250 1.2516 0.02486 0.01511 -0.1071 0.3835 0.5034
7.500 1.2703 0.02508 0.01552 -0.1056 0.3761 0.5522
8.000 1.2975 0.02515 0.01622 -0.1006 0.3606 1.0000
8.250 1.3087 0.02568 0.01685 -0.0980 0.3517 1.0000
8.500 1.3223 0.02617 0.01726 -0.0957 0.3435 1.0000
8.750 1.3335 0.02678 0.01795 -0.0933 0.3347 1.0000
9.000 1.3453 0.02737 0.01851 -0.0910 0.3264 1.0000
9.250 1.3560 0.02807 0.01928 -0.0887 0.3176 1.0000
9.500 1.3659 0.02879 0.01999 -0.0863 0.3090 1.0000
9.750 1.3744 0.02965 0.02091 -0.0840 0.2995 1.0000
10.000 1.3822 0.03054 0.02178 -0.0816 0.2904 1.0000
10.250 1.3892 0.03158 0.02291 -0.0794 0.2804 1.0000
10.500 1.3953 0.03270 0.02402 -0.0771 0.2714 1.0000
10.750 1.4011 0.03394 0.02532 -0.0751 0.2619 1.0000
11.000 1.4056 0.03530 0.02671 -0.0730 0.2529 1.0000
11.250 1.4086 0.03684 0.02827 -0.0710 0.2436 1.0000
11.500 1.4110 0.03854 0.03001 -0.0692 0.2343 1.0000
11.750 1.4112 0.04044 0.03189 -0.0675 0.2261 1.0000
12.000 1.4128 0.04243 0.03394 -0.0660 0.2179 1.0000
12.250 1.4112 0.04470 0.03621 -0.0646 0.2107 1.0000
12.500 1.4110 0.04705 0.03864 -0.0635 0.2034 1.0000
12.750 1.4081 0.04971 0.04130 -0.0626 0.1969 1.0000
13.000 1.4068 0.05241 0.04407 -0.0619 0.1908 1.0000
13.250 1.4042 0.05533 0.04702 -0.0613 0.1850 1.0000
13.500 1.4018 0.05831 0.05000 -0.0609 0.1802 1.0000
13.750 1.4002 0.06139 0.05321 -0.0608 0.1749 1.0000
14.000 1.3970 0.06469 0.05655 -0.0608 0.1697 1.0000
14.250 1.3943 0.06796 0.05983 -0.0608 0.1650 1.0000
14.500 1.3913 0.07151 0.06353 -0.0611 0.1597 1.0000
14.750 1.3869 0.07524 0.06732 -0.0615 0.1544 1.0000
15.000 1.3840 0.07877 0.07085 -0.0619 0.1496 1.0000
15.250 1.3782 0.08302 0.07528 -0.0628 0.1437 1.0000
15.500 1.3733 0.08706 0.07938 -0.0637 0.1384 1.0000
15.750 1.3682 0.09128 0.08370 -0.0647 0.1329 1.0000
16.000 1.3616 0.09587 0.08843 -0.0660 0.1270 1.0000
16.250 1.3567 0.10014 0.09273 -0.0672 0.1219 1.0000
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Polar data table (+)
Polar graphs
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