GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 387 AIRFOIL (goe387-il) Reynolds number: 500,000 Max Cl/Cd: 100.97 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe387-il-500000.txt Download as CSV file: xf-goe387-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 387 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1453 0.10799 0.10560 -0.0648 0.9701 0.0313
-10.750 -0.1296 0.10391 0.10151 -0.0692 0.9597 0.0320
-10.500 -0.1329 0.09421 0.09177 -0.0819 0.9489 0.0336
-10.250 -0.1022 0.09085 0.08839 -0.0861 0.9413 0.0339
-10.000 -0.0680 0.08740 0.08488 -0.0923 0.9320 0.0342
-9.750 -0.0319 0.08366 0.08108 -0.0998 0.9204 0.0348
-9.500 0.0002 0.07941 0.07672 -0.1079 0.9038 0.0358
-9.250 -0.0186 0.06744 0.06457 -0.1230 0.8721 0.0384
-9.000 -0.0040 0.06617 0.06322 -0.1223 0.8539 0.0387
-8.750 0.0060 0.06478 0.06174 -0.1218 0.8368 0.0390
-8.500 0.0097 0.06265 0.05955 -0.1220 0.8213 0.0392
-8.250 0.0120 0.06056 0.05742 -0.1220 0.8078 0.0395
-8.000 0.0073 0.05786 0.05467 -0.1225 0.7946 0.0399
-7.750 -0.0074 0.05468 0.05144 -0.1230 0.7819 0.0401
-7.500 -0.0168 0.05075 0.04745 -0.1244 0.7714 0.0406
-7.250 -0.0864 0.03729 0.03314 -0.1260 0.7610 0.0442
-7.000 -0.0690 0.03574 0.03164 -0.1253 0.7532 0.0445
-6.750 -0.0526 0.03450 0.03034 -0.1244 0.7456 0.0449
-6.500 -0.0365 0.03327 0.02904 -0.1234 0.7387 0.0455
-6.250 -0.0218 0.03180 0.02747 -0.1223 0.7315 0.0464
-6.000 -0.0210 0.02861 0.02365 -0.1195 0.7250 0.0507
-5.750 -0.0002 0.02745 0.02252 -0.1189 0.7185 0.0514
-5.500 0.0203 0.02649 0.02152 -0.1180 0.7119 0.0524
-5.250 0.0326 0.02500 0.01949 -0.1157 0.7057 0.0576
-5.000 0.0548 0.02379 0.01837 -0.1151 0.6988 0.0586
-4.750 0.0767 0.02297 0.01747 -0.1142 0.6919 0.0601
-4.500 0.0953 0.02198 0.01618 -0.1128 0.6860 0.0659
-4.250 0.1140 0.01762 0.01091 -0.1092 0.6809 0.0428
-4.000 0.1378 0.01618 0.00928 -0.1082 0.6756 0.0404
-3.750 0.1630 0.01555 0.00832 -0.1071 0.6706 0.0389
-3.500 0.1883 0.01485 0.00760 -0.1065 0.6654 0.0392
-3.250 0.2139 0.01430 0.00701 -0.1059 0.6600 0.0392
-3.000 0.2397 0.01382 0.00644 -0.1052 0.6550 0.0392
-2.750 0.2656 0.01339 0.00597 -0.1047 0.6503 0.0392
-2.500 0.2909 0.01296 0.00555 -0.1040 0.6451 0.0393
-2.250 0.3159 0.01257 0.00515 -0.1033 0.6398 0.0397
-2.000 0.3412 0.01230 0.00483 -0.1026 0.6347 0.0401
-1.750 0.3661 0.01201 0.00456 -0.1018 0.6295 0.0406
-1.500 0.3910 0.01176 0.00431 -0.1011 0.6241 0.0412
-1.250 0.4161 0.01156 0.00408 -0.1003 0.6190 0.0417
-1.000 0.4415 0.01141 0.00390 -0.0997 0.6141 0.0426
-0.750 0.4667 0.01126 0.00376 -0.0990 0.6085 0.0436
-0.500 0.4911 0.01103 0.00352 -0.0981 0.6028 0.0450
-0.250 0.5163 0.01091 0.00337 -0.0974 0.5972 0.0463
0.000 0.5413 0.01079 0.00326 -0.0967 0.5910 0.0481
0.250 0.5665 0.01072 0.00314 -0.0959 0.5846 0.0504
0.500 0.5915 0.01064 0.00306 -0.0952 0.5787 0.0555
0.750 0.6134 0.01023 0.00302 -0.0940 0.5721 0.1624
1.000 0.6331 0.00975 0.00307 -0.0926 0.5657 0.3507
1.250 0.6476 0.00909 0.00316 -0.0900 0.5594 0.5965
1.500 0.7882 0.00860 0.00348 -0.1140 0.5445 0.9953
1.750 0.8298 0.00868 0.00347 -0.1169 0.5335 1.0000
2.000 0.8515 0.00878 0.00350 -0.1156 0.5241 1.0000
2.250 0.8727 0.00890 0.00354 -0.1142 0.5143 1.0000
2.500 0.8945 0.00901 0.00360 -0.1129 0.5043 1.0000
2.750 0.9149 0.00917 0.00367 -0.1114 0.4943 1.0000
3.000 0.9362 0.00931 0.00376 -0.1100 0.4836 1.0000
3.250 0.9567 0.00948 0.00386 -0.1085 0.4732 1.0000
3.750 0.9966 0.00987 0.00411 -0.1053 0.4515 1.0000
4.000 1.0160 0.01009 0.00425 -0.1036 0.4420 1.0000
4.250 1.0357 0.01029 0.00441 -0.1020 0.4326 1.0000
4.500 1.0552 0.01052 0.00458 -0.1003 0.4243 1.0000
4.750 1.0745 0.01073 0.00475 -0.0987 0.4161 1.0000
5.000 1.0933 0.01097 0.00494 -0.0969 0.4090 1.0000
5.250 1.1132 0.01117 0.00512 -0.0954 0.4022 1.0000
5.500 1.1307 0.01145 0.00534 -0.0934 0.3957 1.0000
5.750 1.1504 0.01165 0.00554 -0.0919 0.3898 1.0000
6.000 1.1692 0.01188 0.00575 -0.0902 0.3842 1.0000
6.250 1.1851 0.01217 0.00599 -0.0879 0.3790 1.0000
6.500 1.2023 0.01237 0.00620 -0.0859 0.3743 1.0000
6.750 1.2189 0.01258 0.00642 -0.0838 0.3691 1.0000
7.000 1.2342 0.01286 0.00667 -0.0815 0.3643 1.0000
7.250 1.2504 0.01316 0.00694 -0.0795 0.3600 1.0000
7.500 1.2692 0.01336 0.00719 -0.0779 0.3560 1.0000
7.750 1.2867 0.01363 0.00747 -0.0761 0.3516 1.0000
8.000 1.3031 0.01396 0.00778 -0.0743 0.3475 1.0000
8.250 1.3197 0.01431 0.00812 -0.0725 0.3433 1.0000
8.500 1.3378 0.01456 0.00843 -0.0710 0.3379 1.0000
8.750 1.3538 0.01493 0.00879 -0.0692 0.3326 1.0000
9.000 1.3682 0.01538 0.00922 -0.0672 0.3270 1.0000
9.250 1.3865 0.01568 0.00958 -0.0659 0.3218 1.0000
9.500 1.4021 0.01612 0.01002 -0.0643 0.3166 1.0000
9.750 1.4155 0.01668 0.01056 -0.0624 0.3114 1.0000
10.000 1.4336 0.01704 0.01100 -0.0612 0.3063 1.0000
10.250 1.4488 0.01756 0.01153 -0.0597 0.3007 1.0000
10.500 1.4611 0.01824 0.01220 -0.0579 0.2953 1.0000
10.750 1.4783 0.01870 0.01274 -0.0568 0.2896 1.0000
11.000 1.4910 0.01941 0.01346 -0.0552 0.2827 1.0000
11.250 1.5044 0.02013 0.01420 -0.0538 0.2756 1.0000
11.500 1.5160 0.02097 0.01506 -0.0523 0.2673 1.0000
11.750 1.5276 0.02185 0.01596 -0.0508 0.2586 1.0000
12.000 1.5348 0.02304 0.01712 -0.0491 0.2477 1.0000
12.250 1.5414 0.02434 0.01839 -0.0475 0.2351 1.0000
12.500 1.5480 0.02568 0.01973 -0.0459 0.2232 1.0000
12.750 1.5527 0.02721 0.02123 -0.0444 0.2127 1.0000
13.000 1.5550 0.02897 0.02296 -0.0427 0.2033 1.0000
13.250 1.5592 0.03064 0.02463 -0.0414 0.1959 1.0000
13.500 1.5622 0.03245 0.02644 -0.0400 0.1903 1.0000
13.750 1.5663 0.03423 0.02825 -0.0388 0.1842 1.0000
14.000 1.5681 0.03623 0.03026 -0.0377 0.1798 1.0000
14.250 1.5731 0.03801 0.03209 -0.0367 0.1755 1.0000
14.500 1.5790 0.03976 0.03389 -0.0359 0.1719 1.0000
14.750 1.5804 0.04194 0.03610 -0.0350 0.1677 1.0000
15.000 1.5800 0.04433 0.03850 -0.0340 0.1640 1.0000
15.250 1.5883 0.04595 0.04022 -0.0335 0.1605 1.0000
15.500 1.5916 0.04809 0.04242 -0.0329 0.1564 1.0000
15.750 1.5906 0.05069 0.04504 -0.0323 0.1524 1.0000
16.000 1.5933 0.05296 0.04737 -0.0319 0.1481 1.0000
16.250 1.5970 0.05519 0.04968 -0.0315 0.1437 1.0000
16.500 1.5960 0.05793 0.05245 -0.0312 0.1395 1.0000
16.750 1.5963 0.06059 0.05517 -0.0309 0.1343 1.0000
17.000 1.5964 0.06334 0.05798 -0.0308 0.1284 1.0000
17.250 1.5918 0.06663 0.06131 -0.0307 0.1225 1.0000
17.500 1.5877 0.06995 0.06466 -0.0308 0.1149 1.0000
17.750 1.5804 0.07371 0.06844 -0.0309 0.1075 1.0000
18.000 1.5689 0.07806 0.07280 -0.0312 0.1010 1.0000
18.250 1.5582 0.08234 0.07712 -0.0316 0.0953 1.0000
18.500 1.5456 0.08696 0.08176 -0.0322 0.0912 1.0000
18.750 1.5366 0.09116 0.08601 -0.0328 0.0878 1.0000
19.000 1.5257 0.09565 0.09055 -0.0336 0.0849 1.0000
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