GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 532 AIRFOIL (goe532-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.7 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe532-il-1000000.txt Download as CSV file: xf-goe532-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 532 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3245 0.12279 0.12099 -0.0271 1.0000 0.0214
-11.750 -0.3202 0.11942 0.11764 -0.0282 1.0000 0.0221
-11.250 -0.3340 0.10730 0.10553 -0.0340 1.0000 0.0233
-11.000 -0.3277 0.10487 0.10311 -0.0344 1.0000 0.0234
-10.750 -0.3202 0.10273 0.10098 -0.0345 1.0000 0.0235
-10.500 -0.3122 0.10084 0.09911 -0.0345 1.0000 0.0238
-10.250 -0.3066 0.09850 0.09679 -0.0348 1.0000 0.0240
-10.000 -0.3025 0.09596 0.09427 -0.0352 1.0000 0.0244
-9.750 -0.2316 0.07455 0.07297 -0.0487 0.9852 0.0270
-9.500 -0.2161 0.07126 0.06968 -0.0514 0.9751 0.0272
-9.250 -0.1952 0.06731 0.06571 -0.0559 0.9649 0.0275
-9.000 -0.3829 0.03514 0.03265 -0.1021 0.9571 0.0268
-8.750 -0.3560 0.03104 0.02840 -0.1069 0.9414 0.0264
-8.500 -0.3499 0.02470 0.02118 -0.1095 0.9112 0.0269
-8.250 -0.3365 0.02133 0.01739 -0.1091 0.8899 0.0271
-8.000 -0.3170 0.01958 0.01539 -0.1085 0.8721 0.0272
-7.750 -0.2944 0.01863 0.01429 -0.1079 0.8563 0.0275
-7.500 -0.2703 0.01799 0.01355 -0.1073 0.8418 0.0278
-7.250 -0.2463 0.01727 0.01270 -0.1067 0.8278 0.0280
-7.000 -0.2219 0.01659 0.01188 -0.1061 0.8138 0.0283
-6.750 -0.1976 0.01583 0.01096 -0.1055 0.7988 0.0286
-6.500 -0.1732 0.01505 0.01001 -0.1048 0.7824 0.0289
-6.250 -0.1481 0.01446 0.00926 -0.1042 0.7638 0.0294
-6.000 -0.1229 0.01390 0.00853 -0.1036 0.7420 0.0298
-5.750 -0.0980 0.01336 0.00779 -0.1028 0.7151 0.0301
-5.500 -0.0731 0.01293 0.00717 -0.1020 0.6845 0.0304
-5.250 -0.0480 0.01260 0.00665 -0.1013 0.6564 0.0306
-5.000 -0.0219 0.01236 0.00625 -0.1007 0.6338 0.0308
-4.750 0.0037 0.01178 0.00555 -0.1002 0.6169 0.0311
-4.500 0.0290 0.01114 0.00483 -0.0996 0.6017 0.0316
-4.250 0.0553 0.01084 0.00448 -0.0991 0.5873 0.0320
-4.000 0.0823 0.01062 0.00421 -0.0987 0.5746 0.0326
-3.750 0.1094 0.01044 0.00398 -0.0984 0.5628 0.0332
-3.500 0.1363 0.01027 0.00373 -0.0980 0.5503 0.0337
-3.250 0.1635 0.01007 0.00348 -0.0976 0.5392 0.0342
-3.000 0.1908 0.00989 0.00326 -0.0972 0.5300 0.0347
-2.750 0.2181 0.00975 0.00306 -0.0969 0.5206 0.0352
-2.500 0.2458 0.00965 0.00291 -0.0966 0.5123 0.0355
-2.250 0.2726 0.00934 0.00255 -0.0962 0.5039 0.0365
-2.000 0.3002 0.00922 0.00240 -0.0959 0.4965 0.0374
-1.750 0.3279 0.00912 0.00228 -0.0957 0.4893 0.0385
-1.500 0.3554 0.00909 0.00220 -0.0953 0.4816 0.0397
-1.250 0.3835 0.00902 0.00212 -0.0951 0.4749 0.0408
-1.000 0.4109 0.00891 0.00197 -0.0948 0.4677 0.0429
-0.750 0.4388 0.00887 0.00191 -0.0946 0.4619 0.0451
-0.500 0.4667 0.00880 0.00184 -0.0943 0.4562 0.0487
-0.250 0.4942 0.00876 0.00179 -0.0940 0.4503 0.0570
0.000 0.5204 0.00825 0.00173 -0.0938 0.4453 0.2109
0.250 0.5470 0.00791 0.00176 -0.0936 0.4404 0.3439
0.500 0.5739 0.00779 0.00180 -0.0933 0.4344 0.4156
0.750 0.6009 0.00773 0.00186 -0.0929 0.4292 0.4743
1.000 0.6282 0.00762 0.00191 -0.0927 0.4240 0.5360
1.250 0.6549 0.00758 0.00198 -0.0923 0.4168 0.5935
1.500 0.6810 0.00749 0.00207 -0.0917 0.4099 0.6720
1.750 0.7061 0.00734 0.00215 -0.0909 0.4037 0.7602
2.000 0.7480 0.00699 0.00223 -0.0937 0.3957 1.0000
2.250 0.7756 0.00707 0.00227 -0.0934 0.3885 1.0000
2.500 0.8024 0.00721 0.00233 -0.0930 0.3795 1.0000
2.750 0.8297 0.00731 0.00239 -0.0928 0.3702 1.0000
3.000 0.8564 0.00745 0.00247 -0.0924 0.3584 1.0000
3.250 0.8828 0.00763 0.00256 -0.0920 0.3428 1.0000
3.500 0.9078 0.00792 0.00269 -0.0914 0.3153 1.0000
3.750 0.9282 0.00861 0.00303 -0.0901 0.2520 1.0000
4.250 0.9743 0.00954 0.00362 -0.0884 0.1970 1.0000
4.500 0.9998 0.00979 0.00381 -0.0878 0.1894 1.0000
4.750 1.0251 0.01003 0.00400 -0.0873 0.1836 1.0000
5.000 1.0505 0.01027 0.00421 -0.0868 0.1787 1.0000
5.250 1.0765 0.01044 0.00437 -0.0864 0.1767 1.0000
5.500 1.1024 0.01062 0.00455 -0.0859 0.1746 1.0000
5.750 1.1279 0.01082 0.00474 -0.0855 0.1721 1.0000
6.000 1.1530 0.01105 0.00494 -0.0849 0.1692 1.0000
6.250 1.1776 0.01130 0.00518 -0.0843 0.1658 1.0000
6.500 1.2022 0.01155 0.00542 -0.0837 0.1630 1.0000
6.750 1.2279 0.01170 0.00559 -0.0833 0.1618 1.0000
7.000 1.2532 0.01187 0.00578 -0.0828 0.1599 1.0000
7.250 1.2780 0.01208 0.00599 -0.0823 0.1572 1.0000
7.500 1.3019 0.01233 0.00622 -0.0816 0.1536 1.0000
7.750 1.3249 0.01264 0.00651 -0.0808 0.1491 1.0000
8.000 1.3500 0.01279 0.00669 -0.0803 0.1465 1.0000
8.250 1.3740 0.01302 0.00690 -0.0797 0.1414 1.0000
8.500 1.3963 0.01333 0.00717 -0.0788 0.1333 1.0000
9.000 1.4269 0.01476 0.00826 -0.0750 0.0871 1.0000
9.250 1.4436 0.01531 0.00879 -0.0733 0.0827 1.0000
9.500 1.4615 0.01576 0.00926 -0.0717 0.0801 1.0000
9.750 1.4784 0.01613 0.00967 -0.0699 0.0790 1.0000
10.000 1.4930 0.01656 0.01014 -0.0678 0.0777 1.0000
10.250 1.5066 0.01705 0.01066 -0.0655 0.0764 1.0000
10.500 1.5187 0.01761 0.01126 -0.0631 0.0750 1.0000
10.750 1.5300 0.01824 0.01192 -0.0607 0.0736 1.0000
11.000 1.5389 0.01901 0.01272 -0.0582 0.0719 1.0000
11.250 1.5480 0.01980 0.01357 -0.0558 0.0707 1.0000
11.500 1.5619 0.02039 0.01421 -0.0541 0.0702 1.0000
11.750 1.5743 0.02109 0.01497 -0.0524 0.0696 1.0000
12.000 1.5857 0.02188 0.01582 -0.0507 0.0689 1.0000
12.250 1.5960 0.02279 0.01678 -0.0490 0.0682 1.0000
12.500 1.6059 0.02378 0.01782 -0.0475 0.0673 1.0000
12.750 1.6150 0.02487 0.01897 -0.0460 0.0662 1.0000
13.000 1.6225 0.02615 0.02029 -0.0445 0.0652 1.0000
13.250 1.6273 0.02771 0.02190 -0.0431 0.0641 1.0000
13.500 1.6275 0.02975 0.02401 -0.0417 0.0627 1.0000
13.750 1.6290 0.03181 0.02614 -0.0406 0.0618 1.0000
14.000 1.6406 0.03305 0.02744 -0.0400 0.0613 1.0000
14.250 1.6500 0.03453 0.02899 -0.0395 0.0606 1.0000
14.500 1.6579 0.03621 0.03073 -0.0390 0.0598 1.0000
14.750 1.6647 0.03805 0.03263 -0.0386 0.0589 1.0000
15.000 1.6699 0.04009 0.03474 -0.0383 0.0582 1.0000
15.250 1.6739 0.04233 0.03703 -0.0381 0.0573 1.0000
15.500 1.6753 0.04492 0.03968 -0.0380 0.0566 1.0000
15.750 1.6742 0.04781 0.04263 -0.0380 0.0559 1.0000
16.000 1.6693 0.05122 0.04612 -0.0382 0.0549 1.0000
16.250 1.6611 0.05511 0.05010 -0.0385 0.0540 1.0000
16.500 1.6660 0.05747 0.05253 -0.0387 0.0537 1.0000
16.750 1.6695 0.06004 0.05518 -0.0390 0.0531 1.0000
17.000 1.6704 0.06295 0.05816 -0.0394 0.0526 1.0000
17.250 1.6720 0.06584 0.06112 -0.0399 0.0519 1.0000
17.500 1.6724 0.06890 0.06426 -0.0405 0.0512 1.0000
17.750 1.6723 0.07207 0.06749 -0.0411 0.0503 1.0000
18.000 1.6703 0.07554 0.07102 -0.0420 0.0496 1.0000
18.250 1.6665 0.07935 0.07488 -0.0430 0.0487 1.0000
18.500 1.6584 0.08381 0.07941 -0.0443 0.0477 1.0000
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