SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 500,000 Max Cl/Cd: 74.33 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8000-il-500000-n5.txt Download as CSV file: xf-sd8000-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD8000-089-88
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7033 0.09935 0.09682 -0.0138 1.0000 0.0062
-12.750 -0.7658 0.08245 0.07987 -0.0234 1.0000 0.0060
-12.500 -0.8270 0.06657 0.06390 -0.0331 1.0000 0.0058
-12.250 -0.8736 0.05152 0.04869 -0.0442 1.0000 0.0056
-12.000 -0.9070 0.04030 0.03721 -0.0557 1.0000 0.0055
-11.750 -0.9258 0.03645 0.03315 -0.0561 1.0000 0.0055
-11.500 -0.9290 0.03337 0.02982 -0.0559 1.0000 0.0056
-11.250 -0.9239 0.03095 0.02717 -0.0554 1.0000 0.0056
-11.000 -0.9157 0.02866 0.02464 -0.0548 1.0000 0.0057
-10.750 -0.9033 0.02680 0.02255 -0.0540 1.0000 0.0059
-10.500 -0.8889 0.02515 0.02068 -0.0532 1.0000 0.0060
-10.250 -0.8728 0.02371 0.01904 -0.0524 1.0000 0.0061
-10.000 -0.8557 0.02244 0.01759 -0.0514 1.0000 0.0062
-9.750 -0.8400 0.02105 0.01603 -0.0502 1.0000 0.0064
-9.500 -0.8236 0.01985 0.01469 -0.0489 1.0000 0.0066
-9.250 -0.8058 0.01894 0.01366 -0.0476 1.0000 0.0069
-9.000 -0.7874 0.01821 0.01284 -0.0463 1.0000 0.0073
-8.750 -0.7675 0.01754 0.01208 -0.0452 0.9997 0.0076
-8.500 -0.7373 0.01677 0.01119 -0.0462 0.9972 0.0082
-8.250 -0.7066 0.01600 0.01028 -0.0473 0.9947 0.0087
-8.000 -0.6770 0.01521 0.00936 -0.0481 0.9919 0.0091
-7.750 -0.6470 0.01448 0.00856 -0.0490 0.9891 0.0099
-7.500 -0.6156 0.01390 0.00791 -0.0500 0.9867 0.0109
-7.250 -0.5832 0.01337 0.00728 -0.0512 0.9848 0.0120
-7.000 -0.5517 0.01281 0.00668 -0.0523 0.9825 0.0136
-6.750 -0.5221 0.01240 0.00621 -0.0528 0.9787 0.0158
-6.500 -0.4914 0.01196 0.00576 -0.0536 0.9753 0.0186
-6.250 -0.4597 0.01161 0.00535 -0.0545 0.9724 0.0213
-6.000 -0.4293 0.01122 0.00496 -0.0551 0.9688 0.0245
-5.750 -0.4006 0.01094 0.00462 -0.0553 0.9638 0.0272
-5.500 -0.3710 0.01060 0.00430 -0.0558 0.9596 0.0325
-5.250 -0.3415 0.01031 0.00402 -0.0561 0.9554 0.0383
-5.000 -0.3145 0.01007 0.00377 -0.0559 0.9493 0.0441
-4.750 -0.2863 0.00981 0.00349 -0.0559 0.9442 0.0500
-4.500 -0.2592 0.00960 0.00326 -0.0557 0.9380 0.0558
-4.250 -0.2323 0.00936 0.00304 -0.0554 0.9313 0.0641
-4.000 -0.2053 0.00916 0.00283 -0.0551 0.9251 0.0723
-3.750 -0.1785 0.00897 0.00264 -0.0547 0.9177 0.0819
-3.500 -0.1517 0.00877 0.00246 -0.0544 0.9110 0.0950
-3.250 -0.1250 0.00857 0.00230 -0.0541 0.9028 0.1100
-3.000 -0.0982 0.00837 0.00213 -0.0537 0.8949 0.1273
-2.750 -0.0715 0.00817 0.00198 -0.0534 0.8858 0.1496
-2.500 -0.0447 0.00797 0.00185 -0.0531 0.8760 0.1743
-2.250 -0.0180 0.00777 0.00172 -0.0527 0.8658 0.2062
-2.000 0.0088 0.00758 0.00160 -0.0524 0.8543 0.2387
-1.750 0.0356 0.00739 0.00150 -0.0521 0.8415 0.2769
-1.500 0.0624 0.00719 0.00141 -0.0518 0.8279 0.3239
-1.250 0.0891 0.00699 0.00133 -0.0515 0.8130 0.3750
-1.000 0.1156 0.00681 0.00127 -0.0512 0.7963 0.4287
-0.750 0.1421 0.00666 0.00122 -0.0508 0.7766 0.4838
-0.500 0.1684 0.00654 0.00118 -0.0503 0.7545 0.5379
-0.250 0.1947 0.00646 0.00117 -0.0499 0.7314 0.5865
0.000 0.2207 0.00640 0.00117 -0.0493 0.7076 0.6354
0.250 0.2465 0.00635 0.00119 -0.0487 0.6815 0.6850
0.500 0.2720 0.00635 0.00122 -0.0481 0.6538 0.7314
0.750 0.2971 0.00638 0.00127 -0.0473 0.6237 0.7735
1.000 0.3218 0.00642 0.00133 -0.0464 0.5931 0.8150
1.250 0.3458 0.00649 0.00139 -0.0453 0.5625 0.8554
1.500 0.3695 0.00659 0.00146 -0.0442 0.5307 0.8937
1.750 0.3955 0.00672 0.00152 -0.0435 0.4981 0.9320
2.000 0.4297 0.00691 0.00159 -0.0448 0.4605 0.9680
2.250 0.4665 0.00716 0.00167 -0.0468 0.4199 0.9992
2.500 0.4923 0.00742 0.00177 -0.0465 0.3868 1.0000
2.750 0.5178 0.00768 0.00190 -0.0461 0.3552 1.0000
3.000 0.5437 0.00793 0.00202 -0.0457 0.3277 1.0000
3.250 0.5696 0.00819 0.00217 -0.0454 0.3006 1.0000
3.500 0.5955 0.00847 0.00233 -0.0450 0.2735 1.0000
3.750 0.6215 0.00874 0.00250 -0.0447 0.2500 1.0000
4.000 0.6474 0.00902 0.00268 -0.0444 0.2259 1.0000
4.250 0.6733 0.00931 0.00288 -0.0441 0.2043 1.0000
4.500 0.6992 0.00960 0.00309 -0.0438 0.1837 1.0000
4.750 0.7250 0.00990 0.00331 -0.0435 0.1658 1.0000
5.000 0.7508 0.01021 0.00354 -0.0431 0.1488 1.0000
5.250 0.7766 0.01050 0.00380 -0.0428 0.1351 1.0000
5.500 0.8024 0.01081 0.00406 -0.0425 0.1225 1.0000
6.000 0.8533 0.01148 0.00463 -0.0418 0.0967 1.0000
6.500 0.9034 0.01223 0.00529 -0.0410 0.0719 1.0000
6.750 0.9287 0.01258 0.00562 -0.0406 0.0638 1.0000
7.000 0.9536 0.01296 0.00599 -0.0402 0.0566 1.0000
7.250 0.9782 0.01336 0.00639 -0.0397 0.0494 1.0000
7.500 1.0029 0.01375 0.00679 -0.0393 0.0436 1.0000
7.750 1.0269 0.01422 0.00724 -0.0387 0.0372 1.0000
8.000 1.0509 0.01468 0.00770 -0.0382 0.0316 1.0000
8.250 1.0745 0.01517 0.00820 -0.0376 0.0268 1.0000
8.500 1.0974 0.01574 0.00878 -0.0369 0.0225 1.0000
8.750 1.1206 0.01624 0.00933 -0.0363 0.0201 1.0000
9.000 1.1429 0.01685 0.00997 -0.0356 0.0180 1.0000
9.250 1.1649 0.01748 0.01065 -0.0348 0.0166 1.0000
9.500 1.1869 0.01807 0.01132 -0.0340 0.0156 1.0000
9.750 1.2083 0.01869 0.01202 -0.0332 0.0147 1.0000
10.000 1.2288 0.01939 0.01277 -0.0322 0.0138 1.0000
10.250 1.2475 0.02026 0.01371 -0.0311 0.0130 1.0000
10.500 1.2662 0.02107 0.01462 -0.0299 0.0125 1.0000
10.750 1.2848 0.02184 0.01549 -0.0288 0.0122 1.0000
11.000 1.3022 0.02267 0.01643 -0.0275 0.0117 1.0000
11.250 1.3187 0.02351 0.01738 -0.0261 0.0113 1.0000
11.500 1.3346 0.02435 0.01831 -0.0247 0.0108 1.0000
11.750 1.3488 0.02525 0.01930 -0.0232 0.0104 1.0000
12.000 1.3586 0.02625 0.02038 -0.0209 0.0101 1.0000
12.250 1.3645 0.02742 0.02166 -0.0183 0.0098 1.0000
12.500 1.3663 0.02891 0.02325 -0.0155 0.0095 1.0000
12.750 1.3700 0.03033 0.02479 -0.0132 0.0092 1.0000
13.000 1.3742 0.03181 0.02641 -0.0113 0.0091 1.0000
13.250 1.3781 0.03339 0.02812 -0.0096 0.0089 1.0000
13.500 1.3821 0.03507 0.02994 -0.0083 0.0086 1.0000
13.750 1.3834 0.03709 0.03210 -0.0072 0.0084 1.0000
14.000 1.3839 0.03934 0.03448 -0.0064 0.0082 1.0000
14.250 1.3815 0.04207 0.03736 -0.0061 0.0080 1.0000
14.500 1.3791 0.04504 0.04046 -0.0063 0.0078 1.0000
14.750 1.3725 0.04880 0.04437 -0.0071 0.0078 1.0000
15.000 1.3648 0.05306 0.04878 -0.0086 0.0077 1.0000
15.250 1.3547 0.05804 0.05391 -0.0108 0.0076 1.0000
15.500 1.3433 0.06363 0.05965 -0.0137 0.0075 1.0000
15.750 1.3302 0.06988 0.06605 -0.0171 0.0074 1.0000
16.000 1.3117 0.07739 0.07373 -0.0214 0.0074 1.0000
16.250 1.2915 0.08553 0.08204 -0.0261 0.0074 1.0000
16.500 1.2702 0.09417 0.09083 -0.0311 0.0074 1.0000
16.750 1.2469 0.10348 0.10029 -0.0365 0.0074 1.0000
17.000 1.2244 0.11278 0.10973 -0.0419 0.0075 1.0000
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Polar data table (+)
Polar graphs
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