GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 398 AIRFOIL (goe398-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.85 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe398-il-1000000.txt Download as CSV file: xf-goe398-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 398 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8136 0.06152 0.05904 -0.0816 1.0000 0.0193
-15.000 -0.8891 0.04580 0.04304 -0.0931 1.0000 0.0190
-14.750 -0.9276 0.03669 0.03370 -0.1014 1.0000 0.0190
-14.500 -0.9606 0.03297 0.02983 -0.1005 1.0000 0.0189
-14.250 -0.9870 0.03129 0.02804 -0.0953 0.9997 0.0190
-14.000 -0.9659 0.02977 0.02638 -0.0971 0.9970 0.0193
-13.750 -0.9414 0.02812 0.02458 -0.0991 0.9943 0.0196
-13.500 -0.9169 0.02687 0.02320 -0.1003 0.9913 0.0198
-13.250 -0.8994 0.02467 0.02082 -0.1013 0.9870 0.0203
-13.000 -0.8727 0.02344 0.01951 -0.1027 0.9846 0.0206
-12.750 -0.8409 0.02281 0.01886 -0.1042 0.9832 0.0210
-12.500 -0.8171 0.02207 0.01807 -0.1042 0.9784 0.0214
-12.250 -0.7890 0.02134 0.01727 -0.1049 0.9749 0.0217
-12.000 -0.7593 0.02055 0.01639 -0.1060 0.9725 0.0222
-11.750 -0.7280 0.01982 0.01557 -0.1073 0.9706 0.0227
-11.500 -0.7036 0.01933 0.01499 -0.1068 0.9636 0.0231
-11.250 -0.6738 0.01832 0.01384 -0.1080 0.9596 0.0236
-11.000 -0.6398 0.01730 0.01277 -0.1100 0.9567 0.0242
-10.750 -0.6112 0.01680 0.01224 -0.1105 0.9481 0.0246
-10.500 -0.5754 0.01627 0.01166 -0.1124 0.9426 0.0251
-10.250 -0.5454 0.01575 0.01106 -0.1130 0.9327 0.0257
-10.000 -0.5138 0.01529 0.01049 -0.1140 0.9232 0.0262
-9.750 -0.4857 0.01489 0.00998 -0.1141 0.9114 0.0267
-9.500 -0.4593 0.01467 0.00965 -0.1137 0.8993 0.0270
-9.250 -0.4397 0.01377 0.00865 -0.1124 0.8865 0.0279
-9.000 -0.4159 0.01343 0.00824 -0.1116 0.8749 0.0284
-8.750 -0.3929 0.01314 0.00790 -0.1106 0.8632 0.0290
-8.500 -0.3695 0.01285 0.00753 -0.1096 0.8526 0.0295
-8.250 -0.3459 0.01259 0.00717 -0.1086 0.8419 0.0301
-8.000 -0.3218 0.01237 0.00688 -0.1077 0.8323 0.0307
-7.500 -0.2768 0.01157 0.00593 -0.1054 0.8138 0.0320
-7.000 -0.2293 0.01103 0.00529 -0.1035 0.7964 0.0333
-6.750 -0.2051 0.01082 0.00502 -0.1026 0.7878 0.0341
-6.500 -0.1801 0.01061 0.00476 -0.1018 0.7798 0.0348
-6.250 -0.1552 0.01046 0.00454 -0.1010 0.7713 0.0355
-6.000 -0.1316 0.01014 0.00417 -0.1000 0.7631 0.0364
-5.750 -0.1077 0.00987 0.00386 -0.0990 0.7544 0.0374
-5.500 -0.0827 0.00969 0.00365 -0.0982 0.7464 0.0384
-5.250 -0.0573 0.00954 0.00346 -0.0975 0.7386 0.0396
-5.000 -0.0317 0.00943 0.00329 -0.0968 0.7316 0.0407
-4.750 -0.0069 0.00918 0.00302 -0.0960 0.7243 0.0423
-4.500 0.0181 0.00904 0.00285 -0.0952 0.7169 0.0441
-4.250 0.0442 0.00891 0.00270 -0.0946 0.7097 0.0459
-4.000 0.0693 0.00876 0.00252 -0.0939 0.7022 0.0487
-3.750 0.0951 0.00864 0.00239 -0.0932 0.6954 0.0523
-3.500 0.1207 0.00850 0.00226 -0.0926 0.6884 0.0584
-3.250 0.1458 0.00839 0.00215 -0.0918 0.6814 0.0666
-3.000 0.1719 0.00826 0.00205 -0.0912 0.6746 0.0766
-2.750 0.1973 0.00817 0.00196 -0.0905 0.6674 0.0865
-2.500 0.2229 0.00807 0.00188 -0.0899 0.6609 0.0983
-2.000 0.2730 0.00784 0.00176 -0.0884 0.6466 0.1441
-1.750 0.2988 0.00772 0.00174 -0.0879 0.6397 0.1726
-1.500 0.3243 0.00768 0.00171 -0.0872 0.6322 0.1914
-1.250 0.3502 0.00763 0.00169 -0.0866 0.6249 0.2076
-1.000 0.3756 0.00758 0.00166 -0.0860 0.6165 0.2240
-0.750 0.4009 0.00753 0.00164 -0.0853 0.6084 0.2436
-0.500 0.4249 0.00741 0.00163 -0.0844 0.5988 0.2871
-0.250 0.4466 0.00714 0.00164 -0.0831 0.5884 0.3932
0.000 0.4684 0.00700 0.00166 -0.0818 0.5761 0.4669
0.250 0.4900 0.00687 0.00169 -0.0804 0.5621 0.5419
0.500 0.5108 0.00675 0.00173 -0.0788 0.5465 0.6139
0.750 0.5284 0.00660 0.00177 -0.0765 0.5288 0.7022
1.250 0.6727 0.00677 0.00230 -0.0958 0.4718 0.9827
1.500 0.7147 0.00701 0.00242 -0.0989 0.4546 0.9897
1.750 0.7574 0.00724 0.00255 -0.1021 0.4410 0.9951
2.000 0.8023 0.00738 0.00262 -0.1059 0.4302 0.9988
2.250 0.8342 0.00751 0.00269 -0.1068 0.4219 1.0000
2.500 0.8563 0.00763 0.00276 -0.1055 0.4146 1.0000
2.750 0.8777 0.00777 0.00285 -0.1042 0.4072 1.0000
3.000 0.9006 0.00787 0.00293 -0.1031 0.4008 1.0000
3.250 0.9223 0.00801 0.00303 -0.1018 0.3941 1.0000
3.500 0.9447 0.00813 0.00312 -0.1006 0.3884 1.0000
3.750 0.9674 0.00824 0.00322 -0.0995 0.3827 1.0000
4.000 0.9889 0.00839 0.00333 -0.0982 0.3763 1.0000
4.250 1.0113 0.00851 0.00344 -0.0970 0.3709 1.0000
4.500 1.0337 0.00864 0.00355 -0.0959 0.3647 1.0000
4.750 1.0545 0.00882 0.00369 -0.0944 0.3579 1.0000
5.000 1.0771 0.00893 0.00380 -0.0933 0.3522 1.0000
5.250 1.0982 0.00909 0.00394 -0.0919 0.3445 1.0000
5.500 1.1191 0.00926 0.00408 -0.0905 0.3363 1.0000
5.750 1.1381 0.00950 0.00425 -0.0888 0.3240 1.0000
6.000 1.1584 0.00969 0.00441 -0.0873 0.3130 1.0000
6.250 1.1775 0.00991 0.00459 -0.0856 0.3021 1.0000
6.500 1.1954 0.01018 0.00480 -0.0837 0.2916 1.0000
6.750 1.2140 0.01041 0.00500 -0.0819 0.2812 1.0000
7.000 1.2308 0.01067 0.00522 -0.0798 0.2715 1.0000
7.250 1.2434 0.01096 0.00546 -0.0768 0.2607 1.0000
7.500 1.2589 0.01119 0.00566 -0.0744 0.2522 1.0000
7.750 1.2728 0.01149 0.00593 -0.0718 0.2432 1.0000
8.000 1.2881 0.01178 0.00619 -0.0695 0.2346 1.0000
8.250 1.3036 0.01209 0.00648 -0.0673 0.2269 1.0000
8.500 1.3196 0.01241 0.00678 -0.0653 0.2196 1.0000
8.750 1.3357 0.01275 0.00711 -0.0633 0.2131 1.0000
9.000 1.3529 0.01306 0.00741 -0.0615 0.2075 1.0000
9.250 1.3675 0.01350 0.00782 -0.0594 0.1997 1.0000
9.500 1.3853 0.01382 0.00815 -0.0579 0.1948 1.0000
9.750 1.4013 0.01423 0.00855 -0.0561 0.1891 1.0000
10.000 1.4172 0.01466 0.00898 -0.0544 0.1837 1.0000
10.250 1.4341 0.01506 0.00939 -0.0529 0.1783 1.0000
10.500 1.4475 0.01564 0.00994 -0.0509 0.1708 1.0000
10.750 1.4638 0.01610 0.01041 -0.0494 0.1644 1.0000
11.000 1.4765 0.01676 0.01104 -0.0475 0.1562 1.0000
11.250 1.4885 0.01748 0.01172 -0.0457 0.1455 1.0000
11.500 1.4962 0.01847 0.01263 -0.0434 0.1280 1.0000
11.750 1.4884 0.02043 0.01433 -0.0395 0.0922 1.0000
12.000 1.4796 0.02260 0.01636 -0.0359 0.0687 1.0000
12.250 1.4841 0.02403 0.01777 -0.0339 0.0616 1.0000
12.500 1.4910 0.02535 0.01910 -0.0322 0.0571 1.0000
12.750 1.4978 0.02671 0.02049 -0.0307 0.0542 1.0000
13.000 1.5033 0.02823 0.02203 -0.0292 0.0513 1.0000
13.250 1.5131 0.02946 0.02331 -0.0281 0.0499 1.0000
13.500 1.5204 0.03090 0.02480 -0.0269 0.0483 1.0000
13.750 1.5258 0.03256 0.02649 -0.0258 0.0468 1.0000
14.000 1.5288 0.03448 0.02846 -0.0246 0.0451 1.0000
14.250 1.5345 0.03621 0.03026 -0.0237 0.0441 1.0000
14.500 1.5419 0.03783 0.03194 -0.0229 0.0433 1.0000
14.750 1.5474 0.03967 0.03384 -0.0222 0.0422 1.0000
15.000 1.5512 0.04174 0.03597 -0.0216 0.0414 1.0000
15.250 1.5524 0.04410 0.03838 -0.0210 0.0404 1.0000
15.500 1.5518 0.04672 0.04106 -0.0204 0.0396 1.0000
15.750 1.5472 0.04986 0.04428 -0.0200 0.0385 1.0000
16.000 1.5508 0.05217 0.04667 -0.0198 0.0381 1.0000
16.250 1.5526 0.05470 0.04928 -0.0196 0.0376 1.0000
16.500 1.5542 0.05732 0.05197 -0.0196 0.0370 1.0000
16.750 1.5534 0.06027 0.05500 -0.0196 0.0363 1.0000
17.000 1.5515 0.06341 0.05820 -0.0198 0.0356 1.0000
17.250 1.5457 0.06709 0.06196 -0.0201 0.0351 1.0000
17.500 1.5384 0.07105 0.06600 -0.0206 0.0345 1.0000
17.750 1.5283 0.07548 0.07052 -0.0213 0.0339 1.0000
18.000 1.5140 0.08057 0.07570 -0.0223 0.0332 1.0000
18.250 1.5090 0.08443 0.07966 -0.0231 0.0330 1.0000
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