SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 500,000 Max Cl/Cd: 80.56 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8000-il-500000.txt Download as CSV file: xf-sd8000-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6598 0.07127 0.06900 -0.0304 1.0000 0.0127
-10.500 -0.7192 0.04914 0.04655 -0.0502 1.0000 0.0120
-10.250 -0.7456 0.04357 0.04084 -0.0540 1.0000 0.0118
-10.000 -0.7624 0.03881 0.03577 -0.0547 1.0000 0.0119
-9.750 -0.7696 0.03444 0.03102 -0.0544 1.0000 0.0119
-9.500 -0.7677 0.03099 0.02720 -0.0534 1.0000 0.0119
-9.250 -0.7595 0.02852 0.02439 -0.0520 1.0000 0.0120
-9.000 -0.7491 0.02646 0.02204 -0.0504 1.0000 0.0121
-8.750 -0.7451 0.02302 0.01820 -0.0481 1.0000 0.0124
-8.500 -0.7329 0.02131 0.01634 -0.0462 1.0000 0.0129
-8.250 -0.7166 0.02050 0.01546 -0.0446 1.0000 0.0134
-8.000 -0.6998 0.01969 0.01455 -0.0429 1.0000 0.0140
-7.750 -0.6830 0.01868 0.01339 -0.0413 1.0000 0.0146
-7.500 -0.6656 0.01763 0.01217 -0.0396 1.0000 0.0152
-7.250 -0.6471 0.01675 0.01114 -0.0381 1.0000 0.0157
-7.000 -0.6295 0.01538 0.00960 -0.0366 1.0000 0.0167
-6.750 -0.5999 0.01457 0.00875 -0.0374 0.9985 0.0181
-6.500 -0.5658 0.01394 0.00803 -0.0390 0.9963 0.0199
-6.250 -0.5318 0.01306 0.00707 -0.0406 0.9943 0.0228
-6.000 -0.4984 0.01273 0.00672 -0.0419 0.9917 0.0262
-5.750 -0.4652 0.01204 0.00599 -0.0432 0.9888 0.0305
-5.500 -0.4297 0.01178 0.00568 -0.0449 0.9864 0.0348
-5.250 -0.3940 0.01124 0.00516 -0.0467 0.9845 0.0418
-5.000 -0.3595 0.01083 0.00475 -0.0482 0.9820 0.0493
-4.750 -0.3265 0.01060 0.00448 -0.0493 0.9783 0.0564
-4.500 -0.2909 0.01022 0.00412 -0.0510 0.9754 0.0672
-4.250 -0.2536 0.00985 0.00379 -0.0531 0.9733 0.0794
-4.000 -0.2154 0.00953 0.00350 -0.0553 0.9716 0.0938
-3.750 -0.1830 0.00922 0.00325 -0.0562 0.9675 0.1110
-3.500 -0.1508 0.00891 0.00303 -0.0572 0.9629 0.1348
-3.250 -0.1171 0.00857 0.00282 -0.0584 0.9591 0.1683
-3.000 -0.0873 0.00825 0.00264 -0.0587 0.9537 0.2104
-2.750 -0.0596 0.00790 0.00249 -0.0587 0.9469 0.2609
-2.500 -0.0318 0.00757 0.00235 -0.0585 0.9407 0.3181
-2.250 -0.0066 0.00725 0.00222 -0.0579 0.9322 0.3821
-2.000 0.0190 0.00695 0.00212 -0.0572 0.9246 0.4452
-1.750 0.0440 0.00666 0.00203 -0.0564 0.9158 0.5122
-1.500 0.0690 0.00641 0.00197 -0.0556 0.9066 0.5741
-1.250 0.0944 0.00619 0.00189 -0.0547 0.8981 0.6310
-1.000 0.1193 0.00599 0.00186 -0.0537 0.8869 0.6861
-0.750 0.1442 0.00582 0.00182 -0.0527 0.8755 0.7361
-0.500 0.1690 0.00567 0.00179 -0.0516 0.8635 0.7819
-0.250 0.1936 0.00556 0.00176 -0.0504 0.8506 0.8245
0.000 0.2176 0.00546 0.00173 -0.0491 0.8366 0.8651
0.250 0.2413 0.00539 0.00171 -0.0476 0.8212 0.9047
0.500 0.2682 0.00536 0.00168 -0.0468 0.8039 0.9420
0.750 0.3042 0.00536 0.00162 -0.0482 0.7837 0.9705
1.000 0.3456 0.00540 0.00156 -0.0508 0.7608 0.9896
1.250 0.3813 0.00548 0.00152 -0.0524 0.7349 1.0000
1.500 0.4049 0.00560 0.00152 -0.0514 0.7073 1.0000
1.750 0.4290 0.00576 0.00154 -0.0505 0.6775 1.0000
2.000 0.4535 0.00594 0.00158 -0.0498 0.6452 1.0000
2.250 0.4782 0.00614 0.00163 -0.0490 0.6102 1.0000
2.500 0.5030 0.00637 0.00170 -0.0483 0.5746 1.0000
2.750 0.5281 0.00662 0.00181 -0.0477 0.5367 1.0000
3.000 0.5531 0.00690 0.00192 -0.0472 0.4993 1.0000
3.250 0.5783 0.00718 0.00205 -0.0466 0.4607 1.0000
3.500 0.6034 0.00749 0.00220 -0.0461 0.4214 1.0000
3.750 0.6287 0.00781 0.00237 -0.0457 0.3848 1.0000
4.000 0.6538 0.00815 0.00255 -0.0452 0.3474 1.0000
4.250 0.6790 0.00850 0.00275 -0.0448 0.3117 1.0000
4.500 0.7042 0.00887 0.00298 -0.0444 0.2789 1.0000
4.750 0.7295 0.00922 0.00321 -0.0440 0.2498 1.0000
5.000 0.7548 0.00959 0.00345 -0.0436 0.2218 1.0000
5.250 0.7802 0.00993 0.00372 -0.0432 0.1979 1.0000
5.500 0.8054 0.01031 0.00401 -0.0428 0.1762 1.0000
5.750 0.8307 0.01068 0.00430 -0.0424 0.1558 1.0000
6.000 0.8555 0.01110 0.00462 -0.0420 0.1371 1.0000
6.250 0.8805 0.01149 0.00496 -0.0415 0.1198 1.0000
6.500 0.9055 0.01188 0.00530 -0.0411 0.1057 1.0000
6.750 0.9302 0.01229 0.00567 -0.0407 0.0933 1.0000
7.000 0.9546 0.01274 0.00607 -0.0402 0.0819 1.0000
7.250 0.9794 0.01313 0.00647 -0.0397 0.0726 1.0000
7.500 1.0039 0.01355 0.00689 -0.0392 0.0638 1.0000
7.750 1.0277 0.01404 0.00737 -0.0386 0.0548 1.0000
8.000 1.0509 0.01462 0.00791 -0.0380 0.0457 1.0000
8.250 1.0729 0.01534 0.00859 -0.0372 0.0370 1.0000
8.500 1.0960 0.01590 0.00919 -0.0365 0.0318 1.0000
8.750 1.1164 0.01678 0.01012 -0.0354 0.0277 1.0000
9.000 1.1386 0.01739 0.01079 -0.0346 0.0253 1.0000
9.250 1.1578 0.01835 0.01177 -0.0334 0.0229 1.0000
9.500 1.1765 0.01931 0.01284 -0.0321 0.0215 1.0000
9.750 1.1965 0.02009 0.01372 -0.0311 0.0204 1.0000
10.000 1.2155 0.02092 0.01465 -0.0299 0.0195 1.0000
10.250 1.2336 0.02180 0.01559 -0.0287 0.0185 1.0000
10.500 1.2484 0.02297 0.01682 -0.0271 0.0176 1.0000
10.750 1.2565 0.02488 0.01887 -0.0247 0.0167 1.0000
11.000 1.2730 0.02574 0.01985 -0.0233 0.0162 1.0000
11.250 1.2864 0.02684 0.02108 -0.0216 0.0157 1.0000
11.500 1.2957 0.02804 0.02242 -0.0193 0.0153 1.0000
11.750 1.3033 0.02924 0.02374 -0.0168 0.0147 1.0000
12.000 1.3090 0.03060 0.02521 -0.0144 0.0144 1.0000
12.250 1.3148 0.03190 0.02661 -0.0123 0.0139 1.0000
12.500 1.3178 0.03355 0.02836 -0.0102 0.0136 1.0000
12.750 1.3191 0.03540 0.03029 -0.0084 0.0132 1.0000
13.000 1.3111 0.03849 0.03355 -0.0065 0.0128 1.0000
13.250 1.2979 0.04251 0.03779 -0.0050 0.0126 1.0000
13.500 1.2954 0.04512 0.04058 -0.0044 0.0124 1.0000
13.750 1.2964 0.04736 0.04299 -0.0045 0.0121 1.0000
14.000 1.2894 0.05103 0.04683 -0.0050 0.0120 1.0000
14.250 1.2804 0.05527 0.05126 -0.0061 0.0119 1.0000
14.500 1.2685 0.06027 0.05644 -0.0081 0.0119 1.0000
14.750 1.2569 0.06564 0.06199 -0.0108 0.0117 1.0000
15.000 1.2438 0.07162 0.06814 -0.0141 0.0116 1.0000
15.250 1.2252 0.07903 0.07574 -0.0185 0.0116 1.0000
15.500 1.2066 0.08690 0.08378 -0.0233 0.0117 1.0000
15.750 1.1867 0.09555 0.09260 -0.0288 0.0116 1.0000
16.000 1.1619 0.10559 0.10281 -0.0351 0.0118 1.0000
16.250 1.1353 0.11668 0.11407 -0.0421 0.0120 1.0000
16.500 1.1056 0.12908 0.12662 -0.0499 0.0121 1.0000
16.750 1.0684 0.14422 0.14191 -0.0592 0.0124 1.0000
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Polar data table (+)
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