GOE 530 AIRFOIL (goe530-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 530 AIRFOIL (goe530-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.45 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe530-il-1000000.txt Download as CSV file: xf-goe530-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3050 0.13142 0.12958 -0.0363 1.0000 0.0264
-13.000 -0.2961 0.12946 0.12764 -0.0366 1.0000 0.0266
-12.750 -0.7875 0.03340 0.03083 -0.0968 0.9785 0.0305
-12.500 -0.7604 0.03243 0.02983 -0.0980 0.9729 0.0307
-12.250 -0.7334 0.03052 0.02779 -0.1004 0.9688 0.0310
-12.000 -0.7048 0.02897 0.02612 -0.1025 0.9629 0.0314
-11.750 -0.6845 0.02574 0.02256 -0.1047 0.9543 0.0318
-11.500 -0.6635 0.02391 0.02049 -0.1052 0.9435 0.0322
-11.250 -0.6452 0.02239 0.01874 -0.1046 0.9328 0.0326
-11.000 -0.6294 0.02117 0.01729 -0.1031 0.9223 0.0329
-10.750 -0.6131 0.02023 0.01617 -0.1013 0.9131 0.0332
-10.500 -0.5947 0.01947 0.01523 -0.0997 0.9044 0.0334
-10.250 -0.5820 0.01813 0.01366 -0.0974 0.8959 0.0338
-10.000 -0.5646 0.01725 0.01266 -0.0956 0.8877 0.0342
-9.750 -0.5427 0.01684 0.01221 -0.0944 0.8808 0.0345
-9.500 -0.5196 0.01662 0.01196 -0.0933 0.8736 0.0349
-9.250 -0.4963 0.01634 0.01161 -0.0922 0.8665 0.0353
-9.000 -0.4738 0.01595 0.01116 -0.0911 0.8592 0.0357
-8.750 -0.4516 0.01549 0.01060 -0.0898 0.8507 0.0361
-8.500 -0.4292 0.01503 0.01002 -0.0886 0.8422 0.0366
-8.250 -0.4064 0.01459 0.00947 -0.0874 0.8328 0.0370
-8.000 -0.3830 0.01420 0.00896 -0.0863 0.8240 0.0374
-7.750 -0.3591 0.01389 0.00855 -0.0853 0.8141 0.0377
-7.500 -0.3377 0.01307 0.00760 -0.0840 0.8047 0.0383
-7.250 -0.3138 0.01274 0.00721 -0.0830 0.7942 0.0389
-7.000 -0.2890 0.01253 0.00696 -0.0821 0.7845 0.0393
-6.750 -0.2642 0.01237 0.00674 -0.0812 0.7738 0.0399
-6.500 -0.2387 0.01220 0.00652 -0.0805 0.7652 0.0405
-6.250 -0.2136 0.01198 0.00622 -0.0797 0.7568 0.0412
-6.000 -0.1880 0.01176 0.00593 -0.0790 0.7491 0.0418
-5.750 -0.1624 0.01158 0.00566 -0.0782 0.7408 0.0423
-5.500 -0.1382 0.01108 0.00509 -0.0773 0.7334 0.0432
-5.250 -0.1123 0.01089 0.00490 -0.0767 0.7261 0.0439
-5.000 -0.0865 0.01077 0.00474 -0.0760 0.7189 0.0446
-4.750 -0.0602 0.01063 0.00457 -0.0754 0.7124 0.0454
-4.500 -0.0340 0.01049 0.00439 -0.0748 0.7052 0.0463
-4.250 -0.0080 0.01042 0.00425 -0.0741 0.6981 0.0472
-4.000 0.0180 0.01010 0.00391 -0.0735 0.6920 0.0482
-3.750 0.0439 0.00995 0.00376 -0.0729 0.6852 0.0492
-3.500 0.0700 0.00988 0.00365 -0.0723 0.6784 0.0501
-3.250 0.0968 0.00977 0.00354 -0.0718 0.6716 0.0512
-3.000 0.1229 0.00969 0.00341 -0.0711 0.6645 0.0523
-2.750 0.1495 0.00963 0.00332 -0.0706 0.6577 0.0531
-2.500 0.1747 0.00934 0.00303 -0.0698 0.6501 0.0546
-2.250 0.2005 0.00932 0.00298 -0.0692 0.6419 0.0559
-2.000 0.2269 0.00926 0.00291 -0.0686 0.6319 0.0573
-1.750 0.2524 0.00922 0.00282 -0.0679 0.6213 0.0585
-1.500 0.2783 0.00920 0.00276 -0.0672 0.6101 0.0594
-1.250 0.3029 0.00898 0.00254 -0.0663 0.6008 0.0613
-1.000 0.3281 0.00897 0.00250 -0.0656 0.5894 0.0629
-0.750 0.3540 0.00893 0.00245 -0.0649 0.5782 0.0645
-0.500 0.3792 0.00893 0.00240 -0.0642 0.5662 0.0659
-0.250 0.4035 0.00890 0.00231 -0.0632 0.5522 0.0672
0.000 0.4274 0.00885 0.00223 -0.0622 0.5361 0.0694
0.250 0.4514 0.00889 0.00221 -0.0613 0.5180 0.0714
0.750 0.4989 0.00904 0.00222 -0.0593 0.4826 0.0746
1.000 0.5221 0.00902 0.00216 -0.0581 0.4677 0.0777
1.250 0.5458 0.00907 0.00217 -0.0572 0.4543 0.0803
1.500 0.5695 0.00914 0.00220 -0.0562 0.4425 0.0827
1.750 0.5931 0.00921 0.00222 -0.0551 0.4315 0.0856
2.000 0.6170 0.00923 0.00224 -0.0542 0.4225 0.0907
2.250 0.6406 0.00929 0.00228 -0.0532 0.4139 0.0957
2.500 0.6641 0.00929 0.00233 -0.0522 0.4066 0.1127
2.750 0.6846 0.00909 0.00243 -0.0507 0.3995 0.2385
3.000 0.6819 0.00805 0.00255 -0.0445 0.3938 0.6967
3.250 0.8142 0.00836 0.00345 -0.0669 0.3785 0.9755
3.500 0.8595 0.00869 0.00372 -0.0705 0.3696 0.9825
3.750 0.9317 0.00902 0.00394 -0.0801 0.3570 0.9879
4.000 0.9764 0.00923 0.00410 -0.0837 0.3475 0.9930
4.250 1.0415 0.00926 0.00402 -0.0919 0.3322 0.9978
4.500 1.0804 0.00938 0.00406 -0.0944 0.3201 1.0000
4.750 1.1019 0.00955 0.00419 -0.0932 0.3099 1.0000
5.000 1.1233 0.00973 0.00432 -0.0919 0.3008 1.0000
5.500 1.1645 0.01014 0.00464 -0.0891 0.2816 1.0000
5.750 1.1838 0.01039 0.00483 -0.0875 0.2719 1.0000
6.000 1.2039 0.01060 0.00500 -0.0860 0.2636 1.0000
6.250 1.2225 0.01085 0.00521 -0.0842 0.2549 1.0000
6.500 1.2421 0.01105 0.00539 -0.0827 0.2487 1.0000
7.000 1.2788 0.01151 0.00582 -0.0791 0.2370 1.0000
7.250 1.2966 0.01174 0.00603 -0.0772 0.2320 1.0000
7.500 1.3127 0.01201 0.00627 -0.0750 0.2267 1.0000
7.750 1.3299 0.01221 0.00648 -0.0730 0.2230 1.0000
8.000 1.3465 0.01242 0.00670 -0.0709 0.2192 1.0000
8.250 1.3608 0.01267 0.00694 -0.0684 0.2150 1.0000
8.500 1.3720 0.01295 0.00721 -0.0653 0.2108 1.0000
8.750 1.3812 0.01312 0.00741 -0.0617 0.2078 1.0000
9.000 1.3907 0.01331 0.00762 -0.0582 0.2048 1.0000
9.250 1.3997 0.01356 0.00787 -0.0547 0.2011 1.0000
9.500 1.4078 0.01388 0.00819 -0.0512 0.1967 1.0000
9.750 1.4191 0.01416 0.00849 -0.0483 0.1936 1.0000
10.000 1.4318 0.01444 0.00879 -0.0457 0.1895 1.0000
10.250 1.4425 0.01481 0.00916 -0.0430 0.1848 1.0000
10.500 1.4527 0.01525 0.00959 -0.0402 0.1797 1.0000
10.750 1.4658 0.01562 0.00998 -0.0379 0.1745 1.0000
11.000 1.4745 0.01621 0.01052 -0.0352 0.1666 1.0000
11.250 1.4860 0.01671 0.01103 -0.0329 0.1585 1.0000
11.500 1.4910 0.01757 0.01179 -0.0299 0.1431 1.0000
11.750 1.4843 0.01910 0.01312 -0.0256 0.1125 1.0000
12.000 1.4743 0.02098 0.01483 -0.0213 0.0889 1.0000
12.250 1.4775 0.02222 0.01605 -0.0188 0.0822 1.0000
12.500 1.4813 0.02349 0.01732 -0.0165 0.0774 1.0000
12.750 1.4899 0.02450 0.01838 -0.0147 0.0751 1.0000
13.000 1.4969 0.02568 0.01959 -0.0130 0.0727 1.0000
13.250 1.5021 0.02702 0.02096 -0.0113 0.0705 1.0000
13.500 1.5057 0.02855 0.02252 -0.0095 0.0679 1.0000
13.750 1.5156 0.02965 0.02368 -0.0084 0.0667 1.0000
14.000 1.5229 0.03100 0.02507 -0.0072 0.0653 1.0000
14.250 1.5282 0.03254 0.02666 -0.0060 0.0638 1.0000
14.500 1.5321 0.03427 0.02843 -0.0048 0.0623 1.0000
14.750 1.5317 0.03646 0.03066 -0.0036 0.0604 1.0000
15.000 1.5387 0.03803 0.03229 -0.0028 0.0595 1.0000
15.250 1.5452 0.03969 0.03401 -0.0021 0.0582 1.0000
15.500 1.5491 0.04165 0.03603 -0.0015 0.0571 1.0000
15.750 1.5511 0.04384 0.03827 -0.0009 0.0560 1.0000
16.000 1.5509 0.04633 0.04081 -0.0003 0.0549 1.0000
16.250 1.5474 0.04924 0.04378 0.0001 0.0537 1.0000
16.500 1.5456 0.05204 0.04666 0.0003 0.0528 1.0000
16.750 1.5493 0.05430 0.04899 0.0004 0.0519 1.0000
17.000 1.5493 0.05703 0.05180 0.0005 0.0511 1.0000
17.250 1.5479 0.05996 0.05479 0.0004 0.0503 1.0000
17.500 1.5443 0.06323 0.05813 0.0001 0.0494 1.0000
17.750 1.5381 0.06690 0.06187 -0.0003 0.0486 1.0000
18.000 1.5293 0.07098 0.06603 -0.0008 0.0480 1.0000
18.250 1.5147 0.07588 0.07101 -0.0017 0.0469 1.0000
18.500 1.5065 0.08004 0.07526 -0.0025 0.0465 1.0000
18.750 1.5033 0.08355 0.07887 -0.0033 0.0459 1.0000
19.000 1.4968 0.08752 0.08292 -0.0042 0.0454 1.0000
19.250 1.4897 0.09161 0.08709 -0.0052 0.0448 1.0000
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