GOE 435 AIRFOIL (goe435-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 435 AIRFOIL (goe435-il) Reynolds number: 200,000 Max Cl/Cd: 52.39 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe435-il-200000.txt Download as CSV file: xf-goe435-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 435 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.5181 0.10003 0.09519 -0.0740 1.0000 0.1080
-15.750 -0.5203 0.09727 0.09249 -0.0755 0.9965 0.1096
-15.500 -0.5042 0.09374 0.08898 -0.0800 0.9887 0.1117
-15.250 -0.4524 0.09526 0.09059 -0.0823 0.9774 0.1127
-15.000 -0.4103 0.09586 0.09123 -0.0845 0.9642 0.1138
-14.750 -0.3852 0.09486 0.09025 -0.0863 0.9500 0.1157
-14.500 -0.6346 0.05751 0.05218 -0.1067 0.9416 0.1369
-14.250 -0.6475 0.05319 0.04769 -0.1093 0.9262 0.1418
-14.000 -0.6723 0.04810 0.04228 -0.1118 0.9126 0.1462
-13.750 -0.6671 0.04639 0.04054 -0.1125 0.8996 0.1493
-13.500 -0.6739 0.04349 0.03746 -0.1139 0.8889 0.1528
-13.250 -0.6878 0.03978 0.03346 -0.1165 0.8777 0.1559
-13.000 -0.6805 0.03839 0.03200 -0.1168 0.8699 0.1583
-12.750 -0.6660 0.03745 0.03108 -0.1177 0.8616 0.1611
-12.500 -0.6597 0.03589 0.02942 -0.1189 0.8534 0.1642
-12.250 -0.6595 0.03396 0.02727 -0.1203 0.8463 0.1669
-12.000 -0.6604 0.03210 0.02518 -0.1222 0.8386 0.1689
-11.750 -0.6427 0.03150 0.02461 -0.1222 0.8321 0.1713
-11.500 -0.6240 0.03119 0.02433 -0.1219 0.8262 0.1739
-11.250 -0.6077 0.03069 0.02375 -0.1224 0.8207 0.1768
-11.000 -0.5918 0.03007 0.02304 -0.1233 0.8145 0.1794
-10.750 -0.5758 0.02949 0.02230 -0.1238 0.8079 0.1817
-10.500 -0.5581 0.02904 0.02164 -0.1241 0.8019 0.1835
-10.250 -0.5337 0.02836 0.02096 -0.1238 0.7968 0.1860
-10.000 -0.5085 0.02813 0.02080 -0.1238 0.7909 0.1884
-9.750 -0.4845 0.02788 0.02057 -0.1238 0.7842 0.1911
-9.500 -0.4612 0.02756 0.02016 -0.1239 0.7781 0.1939
-9.250 -0.4373 0.02718 0.01963 -0.1240 0.7728 0.1961
-9.000 -0.4136 0.02692 0.01923 -0.1243 0.7670 0.1979
-8.750 -0.3898 0.02659 0.01879 -0.1244 0.7602 0.1993
-8.500 -0.3643 0.02582 0.01804 -0.1244 0.7537 0.2013
-8.250 -0.3372 0.02539 0.01760 -0.1243 0.7480 0.2032
-8.000 -0.3104 0.02513 0.01730 -0.1244 0.7422 0.2050
-7.750 -0.2851 0.02483 0.01702 -0.1244 0.7347 0.2071
-7.500 -0.2586 0.02447 0.01659 -0.1244 0.7275 0.2087
-7.250 -0.2309 0.02409 0.01609 -0.1246 0.7212 0.2101
-7.000 -0.2039 0.02383 0.01572 -0.1247 0.7145 0.2114
-6.750 -0.1779 0.02352 0.01537 -0.1247 0.7064 0.2127
-6.500 -0.1500 0.02322 0.01496 -0.1249 0.6995 0.2139
-6.250 -0.1214 0.02289 0.01449 -0.1252 0.6937 0.2152
-6.000 -0.0950 0.02243 0.01407 -0.1252 0.6868 0.2172
-5.750 -0.0683 0.02208 0.01376 -0.1251 0.6793 0.2187
-5.500 -0.0399 0.02176 0.01341 -0.1253 0.6731 0.2201
-5.250 -0.0105 0.02149 0.01306 -0.1255 0.6680 0.2213
-5.000 0.0166 0.02131 0.01288 -0.1256 0.6614 0.2226
-4.750 0.0441 0.02108 0.01265 -0.1256 0.6546 0.2242
-4.500 0.0732 0.02083 0.01234 -0.1259 0.6492 0.2260
-4.250 0.1031 0.02062 0.01204 -0.1263 0.6448 0.2277
-4.000 0.1312 0.02052 0.01191 -0.1265 0.6397 0.2291
-3.750 0.1588 0.02041 0.01179 -0.1266 0.6341 0.2304
-3.500 0.1870 0.02011 0.01153 -0.1267 0.6291 0.2325
-3.250 0.2163 0.01982 0.01126 -0.1270 0.6249 0.2349
-3.000 0.2469 0.01965 0.01104 -0.1274 0.6211 0.2373
-2.750 0.2730 0.01956 0.01104 -0.1273 0.6157 0.2395
-2.500 0.3012 0.01939 0.01089 -0.1274 0.6100 0.2415
-2.250 0.3312 0.01915 0.01058 -0.1277 0.6047 0.2434
-2.000 0.3626 0.01897 0.01030 -0.1282 0.6000 0.2456
-1.750 0.3886 0.01887 0.01031 -0.1281 0.5942 0.2482
-1.500 0.4171 0.01870 0.01021 -0.1283 0.5892 0.2519
-1.250 0.4472 0.01854 0.01006 -0.1288 0.5850 0.2568
-1.000 0.4786 0.01842 0.00989 -0.1294 0.5812 0.2633
-0.750 0.5069 0.01836 0.00995 -0.1298 0.5768 0.2740
-0.500 0.5349 0.01829 0.01008 -0.1301 0.5721 0.2950
-0.250 0.5645 0.01834 0.01030 -0.1305 0.5675 0.3344
0.000 0.5958 0.01851 0.01040 -0.1309 0.5633 0.3647
0.250 0.6281 0.01884 0.01060 -0.1315 0.5593 0.3836
0.500 0.6530 0.01915 0.01107 -0.1310 0.5546 0.3951
0.750 0.6810 0.01946 0.01130 -0.1310 0.5497 0.4061
1.000 0.7095 0.01958 0.01149 -0.1309 0.5450 0.4145
1.250 0.7406 0.01980 0.01162 -0.1313 0.5407 0.4231
1.500 0.7683 0.02015 0.01190 -0.1313 0.5361 0.4306
1.750 0.7924 0.02027 0.01218 -0.1306 0.5309 0.4370
2.000 0.8195 0.02045 0.01238 -0.1304 0.5257 0.4437
2.250 0.8496 0.02061 0.01245 -0.1306 0.5208 0.4508
2.500 0.8795 0.02094 0.01265 -0.1310 0.5158 0.4559
2.750 0.9011 0.02100 0.01287 -0.1301 0.5102 0.4612
3.000 0.9264 0.02114 0.01306 -0.1296 0.5045 0.4668
3.250 0.9554 0.02124 0.01310 -0.1297 0.4991 0.4718
3.500 0.9846 0.02150 0.01327 -0.1300 0.4935 0.4765
3.750 1.0046 0.02169 0.01353 -0.1288 0.4872 0.4802
4.000 1.0295 0.02174 0.01357 -0.1284 0.4809 0.4844
4.250 1.0583 0.02180 0.01359 -0.1285 0.4752 0.4896
4.500 1.0798 0.02204 0.01389 -0.1275 0.4688 0.4940
4.750 1.0988 0.02218 0.01409 -0.1262 0.4615 0.4977
5.000 1.1238 0.02225 0.01409 -0.1258 0.4551 0.5019
5.250 1.1474 0.02247 0.01426 -0.1252 0.4485 0.5059
5.500 1.1618 0.02270 0.01454 -0.1232 0.4407 0.5092
5.750 1.1834 0.02272 0.01455 -0.1223 0.4340 0.5140
6.000 1.1979 0.02298 0.01486 -0.1203 0.4268 0.5186
6.250 1.2067 0.02327 0.01522 -0.1175 0.4190 0.5231
6.500 1.2295 0.02347 0.01529 -0.1168 0.4125 0.5286
6.750 1.2379 0.02411 0.01601 -0.1144 0.4044 0.5328
7.000 1.2538 0.02452 0.01639 -0.1131 0.3973 0.5371
7.250 1.2689 0.02502 0.01692 -0.1117 0.3903 0.5418
7.500 1.2798 0.02572 0.01767 -0.1100 0.3828 0.5469
7.750 1.2999 0.02615 0.01799 -0.1092 0.3767 0.5538
8.000 1.3089 0.02711 0.01902 -0.1075 0.3698 0.5600
8.250 1.3232 0.02780 0.01974 -0.1063 0.3637 0.5671
8.500 1.3432 0.02834 0.02021 -0.1056 0.3582 0.5755
8.750 1.3516 0.02945 0.02142 -0.1041 0.3522 0.5835
9.000 1.3661 0.03026 0.02224 -0.1031 0.3466 0.5922
9.250 1.3885 0.03074 0.02265 -0.1027 0.3414 0.6030
9.500 1.3950 0.03207 0.02411 -0.1012 0.3361 0.6149
9.750 1.4066 0.03309 0.02524 -0.1001 0.3311 0.6290
10.000 1.4282 0.03360 0.02571 -0.0996 0.3265 0.6495
10.250 1.4412 0.03465 0.02687 -0.0986 0.3221 0.6734
10.500 1.4475 0.03604 0.02844 -0.0972 0.3176 0.6998
10.750 1.4587 0.03714 0.02963 -0.0960 0.3134 0.7309
11.000 1.4795 0.03767 0.03011 -0.0954 0.3095 0.7652
11.250 1.4961 0.03846 0.03095 -0.0944 0.3058 0.7960
11.500 1.4972 0.04015 0.03282 -0.0927 0.3023 0.8242
11.750 1.5031 0.04133 0.03417 -0.0910 0.2989 0.8639
12.000 1.5098 0.04210 0.03503 -0.0891 0.2958 1.0000
12.250 1.5318 0.04281 0.03563 -0.0891 0.2927 1.0000
12.500 1.5630 0.04305 0.03572 -0.0895 0.2895 1.0000
12.750 1.5573 0.04557 0.03840 -0.0881 0.2867 1.0000
13.000 1.5585 0.04772 0.04065 -0.0872 0.2836 1.0000
13.250 1.5653 0.04949 0.04245 -0.0866 0.2804 1.0000
13.500 1.5790 0.05070 0.04363 -0.0861 0.2774 1.0000
13.750 1.6026 0.05117 0.04398 -0.0860 0.2745 1.0000
14.000 1.6212 0.05214 0.04492 -0.0857 0.2717 1.0000
14.250 1.6065 0.05567 0.04865 -0.0845 0.2690 1.0000
14.500 1.6008 0.05864 0.05174 -0.0837 0.2662 1.0000
14.750 1.6025 0.06101 0.05418 -0.0832 0.2635 1.0000
15.000 1.6131 0.06257 0.05574 -0.0828 0.2611 1.0000
15.250 1.6317 0.06336 0.05649 -0.0826 0.2589 1.0000
15.500 1.6599 0.06334 0.05637 -0.0824 0.2569 1.0000
15.750 1.6603 0.06595 0.05907 -0.0819 0.2547 1.0000
16.000 1.6250 0.07213 0.06553 -0.0813 0.2522 1.0000
16.250 1.5943 0.07824 0.07187 -0.0811 0.2493 1.0000
16.500 1.5779 0.08300 0.07677 -0.0812 0.2467 1.0000
16.750 1.5822 0.08540 0.07920 -0.0812 0.2446 1.0000
17.000 1.6046 0.08564 0.07938 -0.0810 0.2429 1.0000
17.250 1.6380 0.08461 0.07825 -0.0807 0.2414 1.0000
17.500 1.6662 0.08430 0.07787 -0.0803 0.2396 1.0000
17.750 0.9888 0.19973 0.19514 -0.1241 0.1994 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 435 AIRFOIL (goe435-il)