GOE 382 AIRFOIL (goe382-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 382 AIRFOIL (goe382-il) Reynolds number: 500,000 Max Cl/Cd: 81.88 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe382-il-500000-n5.txt Download as CSV file: xf-goe382-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 382 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5326 0.05510 0.05123 -0.1066 0.8435 0.0255
-13.750 -0.5604 0.04735 0.04316 -0.1136 0.8307 0.0255
-13.500 -0.5729 0.04272 0.03830 -0.1174 0.8173 0.0256
-13.250 -0.5795 0.03936 0.03473 -0.1194 0.8035 0.0256
-13.000 -0.5820 0.03683 0.03198 -0.1203 0.7888 0.0257
-12.750 -0.5816 0.03478 0.02974 -0.1203 0.7735 0.0258
-12.500 -0.5784 0.03309 0.02787 -0.1197 0.7585 0.0258
-12.250 -0.5731 0.03167 0.02626 -0.1185 0.7445 0.0259
-12.000 -0.5676 0.03052 0.02493 -0.1168 0.7317 0.0260
-11.750 -0.5566 0.02938 0.02363 -0.1156 0.7194 0.0261
-11.500 -0.5432 0.02832 0.02241 -0.1146 0.7084 0.0263
-11.250 -0.5282 0.02733 0.02125 -0.1136 0.6973 0.0264
-11.000 -0.5114 0.02639 0.02016 -0.1127 0.6877 0.0266
-10.750 -0.4935 0.02553 0.01914 -0.1119 0.6786 0.0267
-10.500 -0.4744 0.02472 0.01820 -0.1111 0.6714 0.0269
-10.250 -0.4543 0.02397 0.01732 -0.1104 0.6640 0.0272
-9.750 -0.4122 0.02255 0.01563 -0.1091 0.6513 0.0276
-9.500 -0.3901 0.02186 0.01481 -0.1085 0.6454 0.0278
-9.250 -0.3676 0.02124 0.01406 -0.1080 0.6395 0.0279
-9.000 -0.3445 0.02065 0.01335 -0.1074 0.6342 0.0281
-8.750 -0.3207 0.02009 0.01270 -0.1070 0.6289 0.0282
-8.500 -0.2967 0.01959 0.01209 -0.1065 0.6236 0.0284
-8.250 -0.2725 0.01914 0.01153 -0.1061 0.6188 0.0285
-8.000 -0.2476 0.01870 0.01101 -0.1057 0.6149 0.0286
-7.750 -0.2230 0.01814 0.01040 -0.1053 0.6111 0.0288
-7.500 -0.1986 0.01757 0.00981 -0.1049 0.6071 0.0290
-7.250 -0.1740 0.01711 0.00931 -0.1045 0.6030 0.0292
-7.000 -0.1491 0.01671 0.00887 -0.1041 0.5992 0.0294
-6.750 -0.1239 0.01634 0.00847 -0.1037 0.5958 0.0297
-6.500 -0.0981 0.01598 0.00809 -0.1035 0.5925 0.0299
-6.250 -0.0723 0.01564 0.00773 -0.1032 0.5887 0.0302
-6.000 -0.0466 0.01533 0.00739 -0.1028 0.5849 0.0304
-5.750 -0.0208 0.01506 0.00707 -0.1025 0.5813 0.0307
-5.500 0.0050 0.01482 0.00678 -0.1022 0.5778 0.0311
-5.250 0.0315 0.01456 0.00651 -0.1020 0.5746 0.0315
-5.000 0.0581 0.01432 0.00624 -0.1018 0.5708 0.0319
-4.750 0.0847 0.01410 0.00600 -0.1016 0.5669 0.0322
-4.500 0.1111 0.01391 0.00576 -0.1013 0.5632 0.0325
-4.250 0.1369 0.01368 0.00550 -0.1010 0.5595 0.0328
-4.000 0.1633 0.01344 0.00526 -0.1008 0.5559 0.0333
-3.750 0.1901 0.01323 0.00505 -0.1006 0.5518 0.0337
-3.500 0.2169 0.01307 0.00487 -0.1005 0.5475 0.0342
-3.250 0.2436 0.01294 0.00471 -0.1003 0.5435 0.0348
-3.000 0.2701 0.01284 0.00456 -0.1000 0.5394 0.0354
-2.750 0.2976 0.01271 0.00443 -0.1000 0.5353 0.0361
-2.500 0.3247 0.01261 0.00432 -0.0999 0.5303 0.0368
-2.250 0.3513 0.01250 0.00419 -0.0997 0.5254 0.0378
-2.000 0.3776 0.01244 0.00410 -0.0994 0.5209 0.0394
-1.750 0.4050 0.01234 0.00402 -0.0994 0.5164 0.0418
-1.500 0.4316 0.01225 0.00398 -0.0992 0.5107 0.0483
-1.250 0.4578 0.01223 0.00398 -0.0990 0.5050 0.0656
-1.000 0.4848 0.01223 0.00396 -0.0988 0.4997 0.0724
-0.750 0.5116 0.01220 0.00392 -0.0987 0.4940 0.0769
-0.500 0.5377 0.01221 0.00389 -0.0984 0.4882 0.0812
-0.250 0.5637 0.01220 0.00387 -0.0982 0.4828 0.0855
0.000 0.5898 0.01216 0.00385 -0.0980 0.4764 0.0932
0.250 0.6144 0.01210 0.00390 -0.0976 0.4700 0.1441
0.500 0.6403 0.01213 0.00394 -0.0973 0.4644 0.1563
0.750 0.6663 0.01216 0.00397 -0.0971 0.4587 0.1644
1.250 0.7161 0.01223 0.00409 -0.0964 0.4480 0.1987
1.500 0.7402 0.01202 0.00419 -0.0960 0.4425 0.3065
1.750 0.7639 0.01197 0.00428 -0.0956 0.4367 0.3667
2.000 0.7851 0.01162 0.00444 -0.0948 0.4318 0.5499
2.500 0.8333 0.01158 0.00472 -0.0938 0.4228 0.6645
2.750 0.8560 0.01163 0.00489 -0.0930 0.4183 0.7105
3.000 0.8772 0.01168 0.00508 -0.0918 0.4142 0.7637
3.250 0.8985 0.01167 0.00525 -0.0906 0.4102 0.8201
3.500 0.9180 0.01174 0.00547 -0.0890 0.4059 0.8785
3.750 0.9426 0.01193 0.00572 -0.0884 0.4015 0.9382
4.000 0.9782 0.01223 0.00598 -0.0904 0.3973 0.9795
4.250 1.0131 0.01242 0.00616 -0.0923 0.3939 1.0000
4.500 1.0325 0.01261 0.00634 -0.0910 0.3905 1.0000
4.750 1.0520 0.01285 0.00655 -0.0898 0.3869 1.0000
5.000 1.0711 0.01313 0.00679 -0.0886 0.3832 1.0000
5.250 1.0899 0.01345 0.00706 -0.0874 0.3796 1.0000
5.500 1.1122 0.01368 0.00730 -0.0868 0.3766 1.0000
5.750 1.1338 0.01394 0.00756 -0.0861 0.3733 1.0000
6.000 1.1546 0.01425 0.00786 -0.0854 0.3701 1.0000
6.250 1.1747 0.01460 0.00818 -0.0845 0.3669 1.0000
6.500 1.1940 0.01499 0.00855 -0.0836 0.3637 1.0000
6.750 1.2145 0.01536 0.00891 -0.0829 0.3611 1.0000
7.000 1.2360 0.01568 0.00925 -0.0824 0.3582 1.0000
7.250 1.2566 0.01605 0.00964 -0.0818 0.3550 1.0000
7.500 1.2759 0.01649 0.01008 -0.0810 0.3516 1.0000
7.750 1.2945 0.01698 0.01055 -0.0802 0.3486 1.0000
8.000 1.3120 0.01753 0.01109 -0.0793 0.3457 1.0000
8.250 1.3320 0.01798 0.01156 -0.0787 0.3434 1.0000
8.500 1.3522 0.01842 0.01203 -0.0782 0.3409 1.0000
8.750 1.3711 0.01894 0.01258 -0.0776 0.3381 1.0000
9.000 1.3889 0.01952 0.01317 -0.0768 0.3351 1.0000
9.250 1.4052 0.02019 0.01384 -0.0760 0.3320 1.0000
9.500 1.4203 0.02095 0.01459 -0.0750 0.3291 1.0000
9.750 1.4380 0.02158 0.01526 -0.0744 0.3268 1.0000
10.000 1.4559 0.02222 0.01594 -0.0738 0.3241 1.0000
10.250 1.4719 0.02296 0.01672 -0.0731 0.3203 1.0000
10.500 1.4851 0.02390 0.01767 -0.0722 0.3162 1.0000
10.750 1.4958 0.02501 0.01876 -0.0711 0.3120 1.0000
11.000 1.5115 0.02585 0.01965 -0.0705 0.3087 1.0000
11.250 1.5260 0.02678 0.02062 -0.0699 0.3050 1.0000
11.500 1.5376 0.02792 0.02179 -0.0690 0.3009 1.0000
11.750 1.5465 0.02929 0.02315 -0.0680 0.2968 1.0000
12.000 1.5586 0.03047 0.02438 -0.0674 0.2926 1.0000
12.250 1.5695 0.03178 0.02573 -0.0667 0.2877 1.0000
12.500 1.5768 0.03339 0.02735 -0.0658 0.2827 1.0000
12.750 1.5837 0.03505 0.02903 -0.0650 0.2782 1.0000
13.000 1.5938 0.03651 0.03054 -0.0644 0.2734 1.0000
13.250 1.6003 0.03828 0.03234 -0.0637 0.2684 1.0000
13.500 1.6036 0.04036 0.03442 -0.0629 0.2641 1.0000
13.750 1.6131 0.04192 0.03605 -0.0624 0.2602 1.0000
14.000 1.6194 0.04377 0.03795 -0.0619 0.2552 1.0000
14.250 1.6194 0.04624 0.04043 -0.0611 0.2499 1.0000
14.500 1.6243 0.04827 0.04251 -0.0605 0.2448 1.0000
14.750 1.6265 0.05061 0.04488 -0.0600 0.2389 1.0000
15.000 1.6231 0.05348 0.04777 -0.0592 0.2336 1.0000
15.250 1.6272 0.05566 0.04999 -0.0588 0.2277 1.0000
15.500 1.6220 0.05882 0.05317 -0.0581 0.2209 1.0000
15.750 1.6198 0.06170 0.05608 -0.0577 0.2141 1.0000
16.000 1.6117 0.06524 0.05964 -0.0571 0.2062 1.0000
16.250 1.6033 0.06887 0.06329 -0.0566 0.1975 1.0000
16.500 1.5898 0.07314 0.06756 -0.0561 0.1884 1.0000
16.750 1.5763 0.07748 0.07191 -0.0558 0.1788 1.0000
17.000 1.5633 0.08181 0.07626 -0.0555 0.1700 1.0000
17.250 1.5473 0.08659 0.08105 -0.0554 0.1618 1.0000
17.500 1.5324 0.09134 0.08582 -0.0554 0.1535 1.0000
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