GOE 530 AIRFOIL (goe530-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 530 AIRFOIL (goe530-il) Reynolds number: 500,000 Max Cl/Cd: 89.58 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe530-il-500000-n5.txt Download as CSV file: xf-goe530-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 530 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.3104 0.13567 0.13302 -0.0363 1.0000 0.0215
-10.750 -0.5804 0.02509 0.02061 -0.1039 0.8944 0.0329
-10.250 -0.5594 0.02174 0.01666 -0.0994 0.8763 0.0335
-10.000 -0.5396 0.02113 0.01596 -0.0981 0.8688 0.0338
-9.750 -0.5190 0.02063 0.01538 -0.0968 0.8618 0.0341
-9.500 -0.4984 0.02010 0.01477 -0.0955 0.8539 0.0343
-9.250 -0.4768 0.01961 0.01418 -0.0943 0.8467 0.0347
-9.000 -0.4561 0.01902 0.01349 -0.0930 0.8383 0.0350
-8.750 -0.4347 0.01842 0.01274 -0.0917 0.8308 0.0354
-8.500 -0.4132 0.01780 0.01200 -0.0905 0.8231 0.0359
-8.250 -0.3914 0.01718 0.01122 -0.0893 0.8152 0.0365
-8.000 -0.3691 0.01656 0.01042 -0.0882 0.8071 0.0371
-7.750 -0.3467 0.01598 0.00966 -0.0870 0.7971 0.0375
-7.500 -0.3234 0.01558 0.00920 -0.0859 0.7872 0.0379
-7.250 -0.2996 0.01528 0.00883 -0.0849 0.7768 0.0383
-7.000 -0.2753 0.01500 0.00849 -0.0840 0.7674 0.0388
-6.750 -0.2511 0.01474 0.00812 -0.0831 0.7571 0.0393
-6.500 -0.2267 0.01443 0.00773 -0.0822 0.7470 0.0399
-6.000 -0.1774 0.01377 0.00685 -0.0805 0.7288 0.0412
-5.750 -0.1524 0.01346 0.00641 -0.0796 0.7212 0.0419
-5.500 -0.1273 0.01320 0.00612 -0.0789 0.7144 0.0426
-5.250 -0.1017 0.01305 0.00594 -0.0782 0.7068 0.0433
-5.000 -0.0761 0.01290 0.00574 -0.0775 0.7000 0.0440
-4.750 -0.0502 0.01268 0.00548 -0.0769 0.6937 0.0448
-4.500 -0.0245 0.01246 0.00519 -0.0762 0.6867 0.0457
-4.250 0.0010 0.01226 0.00490 -0.0755 0.6799 0.0466
-4.000 0.0268 0.01203 0.00465 -0.0748 0.6729 0.0474
-3.750 0.0527 0.01191 0.00451 -0.0742 0.6660 0.0483
-3.500 0.0785 0.01180 0.00438 -0.0735 0.6596 0.0493
-3.250 0.1047 0.01167 0.00422 -0.0729 0.6522 0.0505
-3.000 0.1302 0.01155 0.00403 -0.0722 0.6443 0.0517
-2.750 0.1560 0.01138 0.00384 -0.0716 0.6372 0.0527
-2.500 0.1815 0.01126 0.00371 -0.0709 0.6290 0.0537
-2.250 0.2070 0.01118 0.00360 -0.0702 0.6209 0.0549
-2.000 0.2327 0.01110 0.00349 -0.0695 0.6116 0.0562
-1.750 0.2579 0.01104 0.00338 -0.0687 0.6025 0.0577
-1.500 0.2828 0.01095 0.00325 -0.0679 0.5909 0.0589
-1.250 0.3072 0.01088 0.00316 -0.0670 0.5768 0.0602
-1.000 0.3312 0.01088 0.00310 -0.0659 0.5599 0.0617
-0.750 0.3548 0.01089 0.00304 -0.0649 0.5414 0.0634
-0.500 0.3785 0.01090 0.00297 -0.0638 0.5251 0.0648
-0.250 0.4014 0.01089 0.00290 -0.0627 0.5071 0.0662
0.000 0.4245 0.01092 0.00288 -0.0615 0.4910 0.0679
0.250 0.4476 0.01097 0.00288 -0.0604 0.4762 0.0699
0.750 0.4939 0.01109 0.00287 -0.0582 0.4489 0.0732
1.000 0.5167 0.01111 0.00287 -0.0571 0.4380 0.0756
1.250 0.5400 0.01116 0.00290 -0.0560 0.4283 0.0783
1.500 0.5635 0.01122 0.00293 -0.0550 0.4203 0.0807
1.750 0.5868 0.01126 0.00296 -0.0540 0.4119 0.0834
2.000 0.6095 0.01133 0.00301 -0.0528 0.4038 0.0874
2.250 0.6330 0.01138 0.00306 -0.0518 0.3959 0.0924
2.500 0.6549 0.01146 0.00313 -0.0506 0.3880 0.1007
2.750 0.6778 0.01144 0.00321 -0.0495 0.3819 0.1297
3.000 0.6986 0.01136 0.00333 -0.0481 0.3749 0.2121
3.250 0.7091 0.01080 0.00350 -0.0447 0.3690 0.5099
3.500 0.8476 0.01072 0.00446 -0.0685 0.3520 0.9770
3.750 0.8953 0.01101 0.00469 -0.0727 0.3419 0.9846
4.000 0.9486 0.01132 0.00492 -0.0782 0.3314 0.9918
4.250 0.9955 0.01150 0.00502 -0.0825 0.3209 0.9958
4.500 1.0363 0.01166 0.00513 -0.0854 0.3117 0.9990
4.750 1.0642 0.01188 0.00528 -0.0856 0.3015 1.0000
5.000 1.0837 0.01210 0.00546 -0.0840 0.2920 1.0000
5.250 1.1017 0.01237 0.00567 -0.0821 0.2825 1.0000
5.500 1.1201 0.01262 0.00587 -0.0803 0.2723 1.0000
5.750 1.1374 0.01289 0.00610 -0.0783 0.2649 1.0000
6.000 1.1550 0.01314 0.00632 -0.0764 0.2570 1.0000
6.250 1.1708 0.01344 0.00658 -0.0742 0.2504 1.0000
6.500 1.1877 0.01367 0.00680 -0.0721 0.2448 1.0000
6.750 1.2032 0.01394 0.00706 -0.0698 0.2392 1.0000
7.000 1.2164 0.01425 0.00734 -0.0671 0.2341 1.0000
7.250 1.2303 0.01448 0.00758 -0.0645 0.2300 1.0000
7.500 1.2405 0.01470 0.00782 -0.0611 0.2264 1.0000
7.750 1.2489 0.01498 0.00809 -0.0575 0.2220 1.0000
8.000 1.2567 0.01531 0.00840 -0.0538 0.2179 1.0000
8.250 1.2687 0.01557 0.00869 -0.0510 0.2141 1.0000
8.500 1.2804 0.01588 0.00901 -0.0482 0.2103 1.0000
8.750 1.2916 0.01624 0.00939 -0.0454 0.2068 1.0000
9.000 1.3016 0.01668 0.00982 -0.0426 0.2029 1.0000
9.250 1.3147 0.01705 0.01021 -0.0402 0.1996 1.0000
9.500 1.3279 0.01744 0.01063 -0.0380 0.1959 1.0000
9.750 1.3397 0.01792 0.01112 -0.0357 0.1915 1.0000
10.000 1.3507 0.01848 0.01168 -0.0333 0.1877 1.0000
10.250 1.3641 0.01895 0.01219 -0.0314 0.1839 1.0000
10.500 1.3769 0.01949 0.01274 -0.0294 0.1788 1.0000
10.750 1.3874 0.02017 0.01342 -0.0273 0.1733 1.0000
11.000 1.3994 0.02080 0.01407 -0.0254 0.1672 1.0000
11.250 1.4086 0.02162 0.01487 -0.0233 0.1592 1.0000
11.500 1.4188 0.02243 0.01568 -0.0215 0.1503 1.0000
11.750 1.4239 0.02360 0.01678 -0.0192 0.1354 1.0000
12.000 1.4178 0.02557 0.01856 -0.0162 0.1053 1.0000
12.250 1.4130 0.02759 0.02048 -0.0135 0.0892 1.0000
12.500 1.4150 0.02921 0.02210 -0.0116 0.0831 1.0000
12.750 1.4192 0.03076 0.02367 -0.0100 0.0793 1.0000
13.000 1.4248 0.03224 0.02521 -0.0087 0.0768 1.0000
13.250 1.4286 0.03393 0.02694 -0.0073 0.0744 1.0000
13.500 1.4313 0.03577 0.02882 -0.0061 0.0723 1.0000
13.750 1.4363 0.03748 0.03060 -0.0051 0.0706 1.0000
14.000 1.4413 0.03923 0.03242 -0.0042 0.0690 1.0000
14.250 1.4447 0.04120 0.03445 -0.0034 0.0674 1.0000
14.500 1.4463 0.04340 0.03671 -0.0026 0.0659 1.0000
14.750 1.4461 0.04586 0.03924 -0.0020 0.0646 1.0000
15.000 1.4443 0.04856 0.04200 -0.0015 0.0633 1.0000
15.250 1.4472 0.05082 0.04434 -0.0011 0.0624 1.0000
15.500 1.4485 0.05331 0.04692 -0.0009 0.0614 1.0000
15.750 1.4486 0.05602 0.04971 -0.0007 0.0604 1.0000
16.000 1.4466 0.05902 0.05279 -0.0007 0.0594 1.0000
16.250 1.4429 0.06229 0.05614 -0.0009 0.0583 1.0000
16.500 1.4381 0.06580 0.05972 -0.0012 0.0574 1.0000
16.750 1.4312 0.06964 0.06364 -0.0016 0.0566 1.0000
17.000 1.4237 0.07362 0.06770 -0.0022 0.0559 1.0000
17.250 1.4204 0.07714 0.07132 -0.0028 0.0553 1.0000
17.500 1.4164 0.08076 0.07504 -0.0034 0.0544 1.0000
17.750 1.4106 0.08468 0.07906 -0.0042 0.0539 1.0000
18.000 1.4049 0.08859 0.08306 -0.0051 0.0531 1.0000
18.250 1.3983 0.09268 0.08723 -0.0061 0.0523 1.0000
18.500 1.3903 0.09703 0.09166 -0.0072 0.0516 1.0000
18.750 1.3825 0.10138 0.09608 -0.0084 0.0509 1.0000
19.000 1.3740 0.10583 0.10059 -0.0097 0.0501 1.0000
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