SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 100,000 Max Cl/Cd: 49.31 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8000-il-100000.txt Download as CSV file: xf-sd8000-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4808 0.09740 0.09237 -0.0167 1.0000 0.1173
-8.750 -0.4996 0.09415 0.08925 -0.0223 1.0000 0.1221
-8.500 -0.5347 0.09018 0.08545 -0.0319 1.0000 0.1230
-8.250 -0.4810 0.08678 0.08192 -0.0206 1.0000 0.1310
-8.000 -0.4946 0.08327 0.07852 -0.0240 1.0000 0.1351
-7.750 -0.5274 0.07797 0.07326 -0.0351 1.0000 0.1370
-7.500 -0.4949 0.07596 0.07133 -0.0253 1.0000 0.1440
-7.250 -0.5611 0.05052 0.04484 -0.0461 1.0000 0.0677
-7.000 -0.5558 0.04581 0.03993 -0.0454 1.0000 0.0670
-6.750 -0.5498 0.04155 0.03521 -0.0444 1.0000 0.0674
-6.500 -0.5403 0.03792 0.03098 -0.0430 1.0000 0.0681
-6.250 -0.5287 0.03355 0.02618 -0.0418 1.0000 0.0689
-6.000 -0.5124 0.03100 0.02360 -0.0407 1.0000 0.0721
-5.750 -0.4944 0.02914 0.02141 -0.0394 1.0000 0.0778
-5.500 -0.4749 0.02667 0.01824 -0.0379 1.0000 0.0817
-5.250 -0.4553 0.02502 0.01666 -0.0370 1.0000 0.0893
-5.000 -0.4335 0.02317 0.01435 -0.0357 1.0000 0.0961
-4.750 -0.4122 0.02204 0.01318 -0.0347 1.0000 0.1063
-4.500 -0.3901 0.02067 0.01173 -0.0337 1.0000 0.1161
-4.250 -0.3679 0.01965 0.01066 -0.0327 1.0000 0.1294
-4.000 -0.3455 0.01870 0.00969 -0.0318 1.0000 0.1440
-3.750 -0.3231 0.01788 0.00889 -0.0309 1.0000 0.1622
-3.500 -0.3006 0.01709 0.00816 -0.0300 1.0000 0.1843
-3.250 -0.2781 0.01636 0.00756 -0.0292 1.0000 0.2127
-3.000 -0.2558 0.01566 0.00708 -0.0284 1.0000 0.2547
-2.750 -0.2342 0.01484 0.00672 -0.0276 1.0000 0.3199
-2.500 -0.2136 0.01402 0.00654 -0.0265 1.0000 0.4359
-2.250 -0.1958 0.01342 0.00658 -0.0245 1.0000 0.5777
-2.000 -0.1803 0.01312 0.00672 -0.0214 1.0000 0.6980
-1.750 -0.1676 0.01294 0.00686 -0.0175 1.0000 0.8073
-1.500 -0.1251 0.01272 0.00677 -0.0193 1.0000 0.9795
-1.250 -0.1016 0.01282 0.00663 -0.0197 1.0000 1.0000
-1.000 -0.0807 0.01300 0.00662 -0.0194 1.0000 1.0000
-0.750 -0.0599 0.01322 0.00668 -0.0191 1.0000 1.0000
-0.500 -0.0394 0.01350 0.00681 -0.0187 1.0000 1.0000
-0.250 0.0120 0.01404 0.00720 -0.0241 0.9890 1.0000
0.000 0.0627 0.01452 0.00756 -0.0292 0.9775 1.0000
0.250 0.1128 0.01491 0.00786 -0.0340 0.9654 1.0000
0.500 0.1628 0.01521 0.00809 -0.0386 0.9529 1.0000
0.750 0.2139 0.01540 0.00825 -0.0432 0.9404 1.0000
1.000 0.2672 0.01544 0.00829 -0.0479 0.9280 1.0000
1.250 0.3172 0.01534 0.00822 -0.0518 0.9140 1.0000
1.500 0.3652 0.01514 0.00806 -0.0550 0.8995 1.0000
1.750 0.4087 0.01486 0.00783 -0.0571 0.8842 1.0000
2.000 0.4448 0.01459 0.00761 -0.0576 0.8664 1.0000
2.250 0.4764 0.01431 0.00737 -0.0572 0.8460 1.0000
2.500 0.5085 0.01395 0.00703 -0.0566 0.8259 1.0000
2.750 0.5350 0.01372 0.00683 -0.0550 0.8010 1.0000
3.000 0.5615 0.01349 0.00660 -0.0535 0.7743 1.0000
3.250 0.5870 0.01335 0.00643 -0.0518 0.7437 1.0000
3.500 0.6120 0.01329 0.00632 -0.0500 0.7092 1.0000
3.750 0.6359 0.01337 0.00629 -0.0483 0.6694 1.0000
4.000 0.6593 0.01355 0.00633 -0.0466 0.6258 1.0000
4.250 0.6820 0.01385 0.00645 -0.0449 0.5786 1.0000
4.500 0.7042 0.01428 0.00666 -0.0433 0.5297 1.0000
4.750 0.7258 0.01480 0.00697 -0.0418 0.4786 1.0000
5.000 0.7471 0.01543 0.00735 -0.0404 0.4294 1.0000
5.250 0.7682 0.01615 0.00781 -0.0390 0.3833 1.0000
5.500 0.7895 0.01693 0.00840 -0.0378 0.3406 1.0000
5.750 0.8109 0.01778 0.00905 -0.0367 0.3030 1.0000
6.000 0.8325 0.01865 0.00976 -0.0357 0.2698 1.0000
6.250 0.8544 0.01957 0.01055 -0.0347 0.2413 1.0000
6.500 0.8766 0.02056 0.01144 -0.0338 0.2170 1.0000
6.750 0.8988 0.02155 0.01236 -0.0330 0.1952 1.0000
7.000 0.9212 0.02268 0.01340 -0.0322 0.1762 1.0000
7.250 0.9432 0.02376 0.01455 -0.0312 0.1580 1.0000
7.500 0.9651 0.02493 0.01576 -0.0303 0.1418 1.0000
7.750 0.9862 0.02612 0.01696 -0.0294 0.1266 1.0000
8.000 1.0071 0.02744 0.01832 -0.0285 0.1127 1.0000
8.250 1.0275 0.02895 0.01993 -0.0274 0.1004 1.0000
8.500 1.0477 0.03069 0.02177 -0.0264 0.0898 1.0000
8.750 1.0691 0.03294 0.02396 -0.0258 0.0817 1.0000
9.000 1.0862 0.03465 0.02612 -0.0241 0.0747 1.0000
9.250 1.1060 0.03748 0.02888 -0.0236 0.0694 1.0000
9.500 1.1181 0.04029 0.03234 -0.0215 0.0667 1.0000
9.750 1.1281 0.04337 0.03591 -0.0196 0.0640 1.0000
10.000 1.1413 0.04565 0.03836 -0.0183 0.0608 1.0000
10.250 1.1524 0.04944 0.04217 -0.0175 0.0580 1.0000
10.500 1.1497 0.05341 0.04663 -0.0152 0.0575 1.0000
10.750 1.1418 0.05747 0.05115 -0.0128 0.0572 1.0000
11.000 1.1297 0.06173 0.05577 -0.0105 0.0572 1.0000
11.250 1.1126 0.06580 0.06011 -0.0082 0.0573 1.0000
11.500 1.0927 0.07010 0.06460 -0.0066 0.0575 1.0000
11.750 1.0723 0.07502 0.06970 -0.0063 0.0577 1.0000
12.000 1.0477 0.07967 0.07458 -0.0075 0.0582 1.0000
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Polar data table (+)
Polar graphs
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