GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 500,000 Max Cl/Cd: 61.76 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe518-il-500000-n5.txt Download as CSV file: xf-goe518-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 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
------ -------- --------- --------- -------- -------- --------
-12.750 0.1158 0.10568 0.10293 -0.1281 0.9442 0.0200
-12.500 0.1296 0.10203 0.09925 -0.1315 0.9405 0.0205
-12.250 0.1197 0.09617 0.09339 -0.1340 0.9338 0.0217
-12.000 0.1511 0.09406 0.09124 -0.1384 0.9271 0.0221
-11.750 0.1608 0.09128 0.08843 -0.1402 0.9177 0.0223
-11.500 0.1821 0.08797 0.08508 -0.1449 0.9111 0.0227
-11.250 0.1900 0.08415 0.08124 -0.1478 0.9024 0.0226
-11.000 0.2087 0.08085 0.07790 -0.1523 0.8957 0.0232
-10.750 0.2176 0.07695 0.07396 -0.1559 0.8878 0.0232
-10.500 0.2271 0.07279 0.06975 -0.1603 0.8791 0.0242
-10.250 0.2273 0.06803 0.06494 -0.1640 0.8689 0.0245
-10.000 0.2251 0.06291 0.05976 -0.1680 0.8582 0.0246
-9.750 0.1856 0.05278 0.04957 -0.1753 0.8447 0.0252
-9.500 0.1084 0.04168 0.03824 -0.1783 0.8287 0.0252
-9.250 0.0984 0.04036 0.03685 -0.1744 0.8183 0.0254
-9.000 0.0617 0.03556 0.03178 -0.1687 0.8077 0.0255
-8.750 0.0444 0.03252 0.02852 -0.1637 0.7975 0.0257
-8.500 0.0232 0.02897 0.02461 -0.1576 0.7879 0.0259
-8.250 0.0143 0.02656 0.02190 -0.1524 0.7772 0.0260
-8.000 0.0185 0.02524 0.02037 -0.1487 0.7667 0.0262
-7.750 0.0208 0.02374 0.01859 -0.1445 0.7538 0.0264
-7.500 0.0264 0.02259 0.01721 -0.1406 0.7390 0.0267
-7.250 0.0311 0.02147 0.01581 -0.1364 0.7200 0.0269
-7.000 0.0377 0.02067 0.01476 -0.1323 0.6997 0.0272
-6.750 0.0432 0.01988 0.01370 -0.1279 0.6784 0.0275
-6.500 0.0496 0.01925 0.01281 -0.1236 0.6594 0.0279
-6.250 0.0553 0.01864 0.01197 -0.1191 0.6433 0.0280
-6.000 0.0622 0.01811 0.01121 -0.1148 0.6290 0.0282
-5.750 0.0730 0.01760 0.01052 -0.1112 0.6159 0.0284
-5.500 0.0849 0.01717 0.00991 -0.1079 0.6034 0.0285
-5.250 0.0967 0.01685 0.00941 -0.1046 0.5916 0.0287
-5.000 0.1117 0.01637 0.00882 -0.1019 0.5797 0.0289
-4.750 0.1264 0.01599 0.00835 -0.0992 0.5690 0.0290
-4.500 0.1421 0.01570 0.00798 -0.0967 0.5572 0.0292
-4.250 0.1582 0.01545 0.00765 -0.0943 0.5465 0.0294
-4.000 0.1732 0.01527 0.00739 -0.0916 0.5346 0.0297
-3.750 0.1904 0.01507 0.00712 -0.0894 0.5224 0.0299
-3.500 0.2063 0.01492 0.00688 -0.0869 0.5100 0.0301
-3.250 0.2218 0.01485 0.00671 -0.0843 0.4973 0.0306
-3.000 0.2383 0.01478 0.00656 -0.0820 0.4836 0.0309
-2.750 0.2548 0.01472 0.00641 -0.0796 0.4708 0.0312
-2.500 0.2707 0.01469 0.00628 -0.0772 0.4581 0.0316
-2.250 0.2870 0.01466 0.00616 -0.0749 0.4460 0.0319
-2.000 0.3043 0.01461 0.00603 -0.0727 0.4354 0.0322
-1.500 0.3399 0.01457 0.00586 -0.0686 0.4173 0.0327
-1.250 0.3570 0.01457 0.00580 -0.0665 0.4092 0.0328
-1.000 0.3745 0.01447 0.00569 -0.0645 0.4024 0.0334
-0.750 0.3927 0.01446 0.00565 -0.0626 0.3951 0.0337
-0.500 0.4101 0.01450 0.00565 -0.0606 0.3889 0.0342
-0.250 0.4300 0.01450 0.00564 -0.0590 0.3833 0.0347
0.000 0.4484 0.01455 0.00565 -0.0572 0.3770 0.0352
0.250 0.4656 0.01465 0.00570 -0.0552 0.3713 0.0359
0.500 0.4855 0.01470 0.00573 -0.0537 0.3662 0.0367
0.750 0.5051 0.01477 0.00578 -0.0521 0.3617 0.0373
1.000 0.5235 0.01485 0.00583 -0.0504 0.3570 0.0380
1.250 0.5412 0.01497 0.00593 -0.0485 0.3529 0.0390
1.500 0.5615 0.01504 0.00600 -0.0472 0.3498 0.0403
1.750 0.5815 0.01514 0.00609 -0.0458 0.3466 0.0417
2.000 0.6008 0.01526 0.00619 -0.0443 0.3431 0.0437
2.250 0.6197 0.01541 0.00633 -0.0427 0.3399 0.0458
2.500 0.6380 0.01558 0.00648 -0.0411 0.3368 0.0499
2.750 0.6557 0.01563 0.00669 -0.0394 0.3342 0.0988
3.000 0.6754 0.01570 0.00686 -0.0381 0.3319 0.1355
3.250 0.6885 0.01523 0.00716 -0.0357 0.3297 0.4243
3.750 0.9561 0.01561 0.00879 -0.0821 0.3188 1.0000
4.000 0.9718 0.01587 0.00902 -0.0801 0.3170 1.0000
4.250 0.9894 0.01608 0.00922 -0.0785 0.3155 1.0000
4.500 1.0069 0.01632 0.00944 -0.0768 0.3139 1.0000
4.750 1.0239 0.01658 0.00969 -0.0752 0.3122 1.0000
5.000 1.0409 0.01686 0.00995 -0.0735 0.3104 1.0000
5.250 1.0580 0.01715 0.01023 -0.0719 0.3088 1.0000
5.500 1.0749 0.01746 0.01052 -0.0703 0.3072 1.0000
5.750 1.0915 0.01779 0.01084 -0.0687 0.3055 1.0000
6.000 1.1078 0.01816 0.01118 -0.0671 0.3040 1.0000
6.250 1.1242 0.01853 0.01153 -0.0655 0.3023 1.0000
6.500 1.1404 0.01894 0.01192 -0.0640 0.3007 1.0000
6.750 1.1583 0.01928 0.01227 -0.0627 0.2995 1.0000
7.000 1.1765 0.01961 0.01262 -0.0615 0.2984 1.0000
7.250 1.1948 0.01995 0.01298 -0.0603 0.2971 1.0000
7.500 1.2127 0.02032 0.01336 -0.0592 0.2957 1.0000
7.750 1.2300 0.02072 0.01377 -0.0580 0.2942 1.0000
8.000 1.2474 0.02113 0.01419 -0.0568 0.2929 1.0000
8.250 1.2646 0.02156 0.01463 -0.0556 0.2915 1.0000
8.500 1.2811 0.02202 0.01511 -0.0544 0.2899 1.0000
8.750 1.2960 0.02258 0.01565 -0.0531 0.2875 1.0000
9.000 1.3120 0.02311 0.01617 -0.0519 0.2861 1.0000
9.250 1.3272 0.02369 0.01675 -0.0506 0.2842 1.0000
9.500 1.3443 0.02418 0.01728 -0.0496 0.2831 1.0000
9.750 1.3616 0.02467 0.01781 -0.0487 0.2819 1.0000
10.000 1.3787 0.02517 0.01836 -0.0478 0.2804 1.0000
10.250 1.3955 0.02571 0.01893 -0.0469 0.2790 1.0000
10.500 1.4112 0.02631 0.01957 -0.0459 0.2772 1.0000
10.750 1.4267 0.02693 0.02022 -0.0450 0.2755 1.0000
11.000 1.4424 0.02757 0.02088 -0.0441 0.2742 1.0000
11.250 1.4571 0.02826 0.02161 -0.0431 0.2729 1.0000
11.500 1.4719 0.02897 0.02234 -0.0422 0.2718 1.0000
11.750 1.4857 0.02974 0.02313 -0.0412 0.2702 1.0000
12.000 1.4979 0.03063 0.02403 -0.0401 0.2678 1.0000
12.250 1.5133 0.03133 0.02480 -0.0393 0.2669 1.0000
12.500 1.5284 0.03207 0.02561 -0.0386 0.2654 1.0000
12.750 1.5424 0.03290 0.02650 -0.0379 0.2636 1.0000
13.000 1.5555 0.03380 0.02746 -0.0371 0.2614 1.0000
13.250 1.5683 0.03473 0.02844 -0.0363 0.2596 1.0000
13.500 1.5795 0.03579 0.02954 -0.0355 0.2577 1.0000
13.750 1.5896 0.03696 0.03073 -0.0346 0.2555 1.0000
14.000 1.5978 0.03828 0.03207 -0.0336 0.2529 1.0000
14.250 1.6103 0.03933 0.03321 -0.0331 0.2504 1.0000
14.500 1.6202 0.04060 0.03456 -0.0324 0.2472 1.0000
14.750 1.6297 0.04192 0.03594 -0.0318 0.2446 1.0000
15.000 1.6364 0.04350 0.03756 -0.0310 0.2418 1.0000
15.250 1.6408 0.04531 0.03940 -0.0303 0.2382 1.0000
15.500 1.6502 0.04672 0.04090 -0.0298 0.2352 1.0000
15.750 1.6556 0.04850 0.04275 -0.0292 0.2311 1.0000
16.000 1.6567 0.05073 0.04501 -0.0286 0.2267 1.0000
16.250 1.6582 0.05298 0.04731 -0.0280 0.2207 1.0000
16.500 1.6555 0.05568 0.05006 -0.0274 0.2142 1.0000
16.750 1.6554 0.05814 0.05257 -0.0270 0.2109 1.0000
17.000 1.6495 0.06124 0.05572 -0.0265 0.2023 1.0000
17.250 1.6377 0.06502 0.05953 -0.0260 0.1943 1.0000
17.500 1.6201 0.06955 0.06408 -0.0256 0.1859 1.0000
17.750 1.5948 0.07508 0.06963 -0.0252 0.1751 1.0000
18.000 1.5773 0.07980 0.07441 -0.0252 0.1684 1.0000
18.250 1.5494 0.08592 0.08057 -0.0253 0.1603 1.0000
18.500 1.5222 0.09210 0.08681 -0.0258 0.1527 1.0000
18.750 1.4997 0.09777 0.09255 -0.0263 0.1476 1.0000
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