GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 200,000 Max Cl/Cd: 79.29 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe439-il-200000.txt Download as CSV file: xf-goe439-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3104 0.09090 0.08783 -0.0267 1.0000 0.0353
-7.000 -0.3234 0.08997 0.08700 -0.0253 1.0000 0.0356
-6.750 -0.3364 0.08906 0.08618 -0.0239 1.0000 0.0357
-6.500 -0.3115 0.08536 0.08246 -0.0345 0.9953 0.0362
-6.250 -0.2730 0.07997 0.07699 -0.0455 0.9886 0.0364
-6.000 -0.2585 0.07283 0.06989 -0.0476 0.9845 0.0375
-5.750 -0.2361 0.06903 0.06607 -0.0493 0.9786 0.0390
-5.500 -0.2028 0.06474 0.06173 -0.0557 0.9727 0.0411
-5.250 -0.1660 0.06009 0.05700 -0.0639 0.9654 0.0442
-5.000 -0.0957 0.05429 0.05076 -0.0819 0.9583 0.0485
-4.750 -0.0820 0.04915 0.04577 -0.0824 0.9522 0.0515
-4.500 -0.0461 0.04573 0.04225 -0.0870 0.9462 0.0560
-4.250 0.0080 0.03951 0.03559 -0.0972 0.9425 0.0633
-4.000 0.0345 0.03704 0.03310 -0.0984 0.9332 0.0662
-3.750 0.0785 0.03295 0.02858 -0.1037 0.9283 0.0766
-3.500 0.1058 0.03083 0.02642 -0.1044 0.9180 0.0815
-3.250 0.1380 0.02848 0.02385 -0.1061 0.9092 0.0944
-3.000 0.1795 0.01889 0.01257 -0.1066 0.9017 0.0477
-2.750 0.2084 0.01650 0.00970 -0.1066 0.8913 0.0505
-2.500 0.2383 0.01552 0.00856 -0.1066 0.8812 0.0566
-2.250 0.2692 0.01451 0.00722 -0.1065 0.8714 0.0616
-2.000 0.2960 0.01369 0.00636 -0.1060 0.8589 0.0708
-1.750 0.3230 0.01308 0.00567 -0.1054 0.8464 0.0793
-1.500 0.3501 0.01270 0.00519 -0.1048 0.8338 0.0903
-1.250 0.3768 0.01236 0.00481 -0.1042 0.8210 0.1048
-1.000 0.4033 0.01201 0.00443 -0.1035 0.8081 0.1294
-0.750 0.4290 0.01156 0.00407 -0.1029 0.7951 0.1648
-0.500 0.4548 0.01133 0.00385 -0.1023 0.7818 0.1963
-0.250 0.4805 0.01111 0.00368 -0.1017 0.7683 0.2310
0.000 0.4999 0.00996 0.00368 -0.1002 0.7551 0.5939
0.250 0.5459 0.00927 0.00346 -0.1033 0.7407 1.0000
0.500 0.5714 0.00938 0.00338 -0.1025 0.7260 1.0000
0.750 0.5968 0.00950 0.00334 -0.1018 0.7110 1.0000
1.000 0.6222 0.00963 0.00333 -0.1011 0.6957 1.0000
1.250 0.6475 0.00976 0.00333 -0.1004 0.6803 1.0000
1.500 0.6728 0.00989 0.00334 -0.0997 0.6647 1.0000
1.750 0.6980 0.01003 0.00337 -0.0990 0.6489 1.0000
2.000 0.7233 0.01018 0.00341 -0.0983 0.6333 1.0000
2.250 0.7485 0.01034 0.00347 -0.0976 0.6178 1.0000
2.500 0.7737 0.01052 0.00355 -0.0970 0.6025 1.0000
2.750 0.7988 0.01072 0.00364 -0.0964 0.5875 1.0000
3.000 0.8240 0.01093 0.00377 -0.0957 0.5729 1.0000
3.250 0.8490 0.01116 0.00394 -0.0951 0.5585 1.0000
3.500 0.8741 0.01141 0.00412 -0.0946 0.5447 1.0000
3.750 0.8991 0.01167 0.00433 -0.0940 0.5311 1.0000
4.000 0.9239 0.01193 0.00455 -0.0934 0.5173 1.0000
4.250 0.9486 0.01220 0.00481 -0.0928 0.5036 1.0000
4.500 0.9733 0.01248 0.00507 -0.0922 0.4903 1.0000
4.750 0.9980 0.01277 0.00535 -0.0916 0.4780 1.0000
5.000 1.0226 0.01307 0.00564 -0.0910 0.4659 1.0000
5.250 1.0466 0.01334 0.00594 -0.0903 0.4520 1.0000
5.500 1.0701 0.01360 0.00620 -0.0895 0.4370 1.0000
5.750 1.0933 0.01385 0.00648 -0.0886 0.4217 1.0000
6.000 1.1157 0.01410 0.00672 -0.0876 0.4039 1.0000
6.250 1.1377 0.01438 0.00701 -0.0866 0.3860 1.0000
6.500 1.1592 0.01462 0.00729 -0.0855 0.3628 1.0000
6.750 1.1797 0.01494 0.00760 -0.0842 0.3360 1.0000
7.000 1.1984 0.01540 0.00796 -0.0827 0.2986 1.0000
7.250 1.2092 0.01656 0.00861 -0.0802 0.2079 1.0000
7.500 1.2034 0.01956 0.01050 -0.0758 0.0521 1.0000
7.750 1.2159 0.02085 0.01177 -0.0734 0.0399 1.0000
8.000 1.2282 0.02205 0.01313 -0.0710 0.0356 1.0000
8.250 1.2334 0.02363 0.01488 -0.0677 0.0321 1.0000
8.500 1.2414 0.02477 0.01617 -0.0648 0.0309 1.0000
8.750 1.2449 0.02610 0.01762 -0.0612 0.0299 1.0000
9.000 1.2472 0.02758 0.01922 -0.0578 0.0290 1.0000
9.250 1.2496 0.02921 0.02095 -0.0547 0.0283 1.0000
9.500 1.2528 0.03098 0.02280 -0.0519 0.0276 1.0000
9.750 1.2580 0.03278 0.02470 -0.0496 0.0267 1.0000
10.000 1.2641 0.03476 0.02672 -0.0476 0.0253 1.0000
10.250 1.2764 0.03703 0.02898 -0.0460 0.0240 1.0000
10.500 1.3047 0.03954 0.03153 -0.0456 0.0236 1.0000
10.750 1.3369 0.04226 0.03440 -0.0459 0.0236 1.0000
11.000 1.3562 0.04441 0.03679 -0.0448 0.0240 1.0000
11.250 1.3712 0.04687 0.03971 -0.0428 0.0260 1.0000
11.500 1.3828 0.05072 0.04400 -0.0409 0.0278 1.0000
11.750 1.3852 0.05420 0.04783 -0.0388 0.0285 1.0000
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Polar data table (+)
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