GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 387 AIRFOIL (goe387-il) Reynolds number: 200,000 Max Cl/Cd: 69.79 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe387-il-200000-n5.txt Download as CSV file: xf-goe387-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0523 0.09415 0.09016 -0.0894 0.9083 0.0484
-9.750 -0.0521 0.08698 0.08291 -0.1013 0.8917 0.0504
-9.500 -0.0327 0.08313 0.07900 -0.1050 0.8778 0.0506
-9.250 -0.0077 0.08089 0.07669 -0.1064 0.8652 0.0513
-9.000 0.0079 0.07809 0.07382 -0.1088 0.8512 0.0518
-8.750 0.0180 0.07544 0.07110 -0.1105 0.8368 0.0526
-8.500 0.0224 0.07259 0.06821 -0.1118 0.8233 0.0530
-8.250 0.0245 0.06971 0.06528 -0.1131 0.8113 0.0538
-7.750 -0.1205 0.04062 0.03530 -0.1247 0.7824 0.0341
-7.500 -0.1157 0.03816 0.03263 -0.1236 0.7744 0.0340
-7.250 -0.1102 0.03567 0.02987 -0.1221 0.7661 0.0339
-7.000 -0.1019 0.03328 0.02715 -0.1207 0.7593 0.0338
-6.750 -0.0916 0.03118 0.02476 -0.1191 0.7516 0.0337
-6.500 -0.0785 0.02927 0.02249 -0.1175 0.7450 0.0337
-6.250 -0.0624 0.02767 0.02057 -0.1161 0.7388 0.0338
-6.000 -0.0451 0.02626 0.01887 -0.1147 0.7320 0.0338
-5.750 -0.0258 0.02504 0.01734 -0.1134 0.7261 0.0340
-5.500 -0.0057 0.02409 0.01603 -0.1121 0.7203 0.0343
-5.250 0.0157 0.02295 0.01480 -0.1112 0.7138 0.0347
-5.000 0.0388 0.02212 0.01386 -0.1105 0.7080 0.0351
-4.750 0.0622 0.02137 0.01299 -0.1097 0.7023 0.0355
-4.500 0.0854 0.02061 0.01210 -0.1088 0.6959 0.0356
-4.250 0.1096 0.01992 0.01124 -0.1080 0.6900 0.0358
-4.000 0.1342 0.01929 0.01048 -0.1072 0.6843 0.0360
-3.750 0.1583 0.01871 0.00982 -0.1064 0.6773 0.0363
-3.500 0.1832 0.01818 0.00917 -0.1056 0.6708 0.0366
-3.250 0.2078 0.01770 0.00862 -0.1048 0.6641 0.0369
-3.000 0.2322 0.01727 0.00813 -0.1040 0.6573 0.0373
-2.750 0.2574 0.01688 0.00765 -0.1033 0.6518 0.0378
-2.500 0.2820 0.01652 0.00727 -0.1026 0.6460 0.0382
-2.250 0.3066 0.01624 0.00694 -0.1018 0.6399 0.0389
-2.000 0.3308 0.01587 0.00657 -0.1010 0.6345 0.0399
-1.750 0.3551 0.01559 0.00630 -0.1002 0.6291 0.0409
-1.500 0.3791 0.01535 0.00607 -0.0993 0.6230 0.0418
-1.250 0.4037 0.01516 0.00583 -0.0986 0.6173 0.0426
-1.000 0.4286 0.01500 0.00561 -0.0978 0.6118 0.0434
-0.750 0.4528 0.01486 0.00545 -0.0970 0.6052 0.0444
-0.500 0.4774 0.01470 0.00525 -0.0962 0.5992 0.0457
-0.250 0.5024 0.01459 0.00510 -0.0954 0.5937 0.0476
0.000 0.5267 0.01450 0.00501 -0.0946 0.5870 0.0502
0.250 0.5511 0.01438 0.00488 -0.0938 0.5808 0.0559
0.500 0.5735 0.01405 0.00483 -0.0927 0.5743 0.1229
0.750 0.5947 0.01370 0.00486 -0.0915 0.5670 0.2362
1.000 0.6168 0.01347 0.00487 -0.0904 0.5604 0.3337
1.250 0.6363 0.01315 0.00494 -0.0888 0.5528 0.4459
1.750 0.7914 0.01238 0.00529 -0.1095 0.5330 1.0000
2.000 0.8129 0.01252 0.00531 -0.1081 0.5254 1.0000
2.250 0.8341 0.01266 0.00539 -0.1068 0.5163 1.0000
2.500 0.8548 0.01281 0.00544 -0.1053 0.5073 1.0000
2.750 0.8752 0.01297 0.00553 -0.1038 0.4969 1.0000
3.000 0.8954 0.01316 0.00562 -0.1022 0.4874 1.0000
3.250 0.9153 0.01335 0.00572 -0.1006 0.4776 1.0000
3.500 0.9353 0.01355 0.00586 -0.0991 0.4684 1.0000
3.750 0.9544 0.01378 0.00599 -0.0974 0.4593 1.0000
4.000 0.9741 0.01400 0.00616 -0.0958 0.4503 1.0000
4.250 0.9926 0.01426 0.00633 -0.0940 0.4420 1.0000
4.500 1.0120 0.01450 0.00653 -0.0924 0.4338 1.0000
4.750 1.0301 0.01478 0.00673 -0.0906 0.4261 1.0000
5.000 1.0489 0.01504 0.00696 -0.0889 0.4188 1.0000
5.250 1.0668 0.01533 0.00720 -0.0871 0.4115 1.0000
5.500 1.0847 0.01562 0.00744 -0.0853 0.4055 1.0000
5.750 1.1029 0.01590 0.00772 -0.0836 0.3990 1.0000
6.000 1.1196 0.01622 0.00799 -0.0816 0.3931 1.0000
6.250 1.1359 0.01653 0.00827 -0.0795 0.3878 1.0000
6.500 1.1522 0.01682 0.00857 -0.0775 0.3823 1.0000
6.750 1.1675 0.01716 0.00888 -0.0753 0.3770 1.0000
7.000 1.1833 0.01752 0.00920 -0.0733 0.3724 1.0000
7.250 1.1999 0.01784 0.00956 -0.0715 0.3672 1.0000
7.500 1.2156 0.01821 0.00994 -0.0695 0.3618 1.0000
7.750 1.2310 0.01863 0.01032 -0.0676 0.3572 1.0000
8.000 1.2477 0.01901 0.01074 -0.0660 0.3528 1.0000
8.250 1.2639 0.01942 0.01118 -0.0643 0.3480 1.0000
8.500 1.2791 0.01987 0.01165 -0.0625 0.3432 1.0000
8.750 1.2941 0.02038 0.01213 -0.0608 0.3390 1.0000
9.000 1.3099 0.02084 0.01266 -0.0592 0.3342 1.0000
9.250 1.3250 0.02135 0.01323 -0.0576 0.3295 1.0000
9.500 1.3392 0.02191 0.01381 -0.0559 0.3251 1.0000
9.750 1.3533 0.02252 0.01441 -0.0543 0.3209 1.0000
10.000 1.3676 0.02311 0.01510 -0.0528 0.3158 1.0000
10.250 1.3795 0.02381 0.01585 -0.0511 0.3100 1.0000
10.500 1.3898 0.02462 0.01664 -0.0493 0.3040 1.0000
10.750 1.4009 0.02542 0.01754 -0.0477 0.2969 1.0000
11.000 1.4095 0.02638 0.01850 -0.0459 0.2901 1.0000
11.250 1.4197 0.02733 0.01953 -0.0444 0.2832 1.0000
11.500 1.4277 0.02842 0.02065 -0.0428 0.2758 1.0000
11.750 1.4360 0.02956 0.02184 -0.0413 0.2686 1.0000
12.000 1.4432 0.03081 0.02314 -0.0399 0.2608 1.0000
12.250 1.4500 0.03213 0.02451 -0.0385 0.2530 1.0000
12.500 1.4546 0.03367 0.02607 -0.0371 0.2445 1.0000
12.750 1.4606 0.03516 0.02762 -0.0359 0.2366 1.0000
13.000 1.4632 0.03695 0.02942 -0.0346 0.2290 1.0000
13.250 1.4671 0.03873 0.03125 -0.0336 0.2202 1.0000
13.500 1.4683 0.04078 0.03331 -0.0325 0.2127 1.0000
13.750 1.4700 0.04285 0.03542 -0.0315 0.2054 1.0000
14.000 1.4697 0.04516 0.03774 -0.0306 0.1989 1.0000
14.250 1.4720 0.04731 0.03993 -0.0298 0.1936 1.0000
14.500 1.4706 0.04984 0.04248 -0.0290 0.1884 1.0000
14.750 1.4728 0.05208 0.04478 -0.0284 0.1842 1.0000
15.000 1.4747 0.05439 0.04715 -0.0279 0.1799 1.0000
15.250 1.4737 0.05704 0.04983 -0.0274 0.1756 1.0000
15.500 1.4738 0.05961 0.05243 -0.0270 0.1717 1.0000
15.750 1.4761 0.06202 0.05494 -0.0267 0.1677 1.0000
16.000 1.4745 0.06489 0.05787 -0.0265 0.1631 1.0000
16.250 1.4725 0.06778 0.06077 -0.0263 0.1593 1.0000
16.500 1.4733 0.07051 0.06362 -0.0263 0.1552 1.0000
16.750 1.4714 0.07361 0.06682 -0.0264 0.1504 1.0000
17.000 1.4673 0.07696 0.07019 -0.0266 0.1459 1.0000
17.250 1.4654 0.08016 0.07349 -0.0269 0.1414 1.0000
17.500 1.4620 0.08364 0.07709 -0.0273 0.1362 1.0000
17.750 1.4564 0.08738 0.08088 -0.0279 0.1317 1.0000
18.000 1.4528 0.09096 0.08459 -0.0285 0.1262 1.0000
18.250 1.4472 0.09483 0.08853 -0.0292 0.1210 1.0000
18.500 1.4412 0.09881 0.09259 -0.0301 0.1158 1.0000
18.750 1.4344 0.10295 0.09680 -0.0311 0.1103 1.0000
19.000 1.4269 0.10720 0.10111 -0.0322 0.1054 1.0000
19.250 1.4196 0.11146 0.10542 -0.0334 0.1006 1.0000
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