SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 50,000 Max Cl/Cd: 33.57 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8000-il-50000.txt Download as CSV file: xf-sd8000-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4577 0.09509 0.08820 -0.0044 1.0000 0.3126
-7.750 -0.4564 0.09224 0.08540 -0.0038 1.0000 0.3279
-7.500 -0.4580 0.08952 0.08274 -0.0031 1.0000 0.3434
-7.250 -0.4544 0.08636 0.07964 -0.0021 1.0000 0.3582
-7.000 -0.4590 0.08388 0.07725 -0.0008 1.0000 0.3737
-6.750 -0.4300 0.07917 0.07248 0.0011 1.0000 0.3998
-6.500 -0.5206 0.05653 0.04937 -0.0392 1.0000 0.1511
-6.250 -0.5117 0.05195 0.04461 -0.0393 1.0000 0.1498
-6.000 -0.5012 0.04730 0.03967 -0.0394 1.0000 0.1478
-5.750 -0.4888 0.04277 0.03470 -0.0395 1.0000 0.1468
-5.500 -0.4741 0.03879 0.02998 -0.0394 1.0000 0.1509
-5.250 -0.4561 0.03590 0.02697 -0.0384 1.0000 0.1572
-5.000 -0.4362 0.03302 0.02342 -0.0378 1.0000 0.1657
-4.750 -0.4158 0.03083 0.02112 -0.0367 1.0000 0.1772
-4.500 -0.3943 0.02879 0.01884 -0.0357 1.0000 0.1911
-4.250 -0.3718 0.02695 0.01673 -0.0348 1.0000 0.2075
-4.000 -0.3496 0.02539 0.01509 -0.0337 1.0000 0.2285
-3.750 -0.3266 0.02396 0.01357 -0.0327 1.0000 0.2529
-3.500 -0.3043 0.02271 0.01236 -0.0315 1.0000 0.2860
-3.250 -0.2817 0.02150 0.01128 -0.0303 1.0000 0.3287
-3.000 -0.2603 0.02032 0.01045 -0.0288 1.0000 0.3903
-2.750 -0.2407 0.01910 0.00987 -0.0267 1.0000 0.4900
-2.500 -0.2288 0.01805 0.00968 -0.0220 1.0000 0.6333
-2.250 -0.2255 0.01743 0.00966 -0.0144 1.0000 0.7801
-2.000 -0.1278 0.01708 0.00899 -0.0243 1.0000 1.0000
-1.750 -0.1254 0.01677 0.00839 -0.0221 1.0000 1.0000
-1.500 -0.1099 0.01672 0.00801 -0.0212 1.0000 1.0000
-1.250 -0.0913 0.01677 0.00778 -0.0205 1.0000 1.0000
-1.000 -0.0718 0.01689 0.00765 -0.0200 1.0000 1.0000
-0.750 -0.0519 0.01705 0.00760 -0.0194 1.0000 1.0000
-0.500 -0.0319 0.01726 0.00761 -0.0189 1.0000 1.0000
-0.250 -0.0119 0.01751 0.00771 -0.0184 1.0000 1.0000
0.000 0.0080 0.01781 0.00787 -0.0179 1.0000 1.0000
0.250 0.0276 0.01815 0.00809 -0.0175 1.0000 1.0000
0.500 0.0470 0.01855 0.00838 -0.0171 1.0000 1.0000
0.750 0.0660 0.01900 0.00875 -0.0168 1.0000 1.0000
1.000 0.0846 0.01950 0.00919 -0.0165 1.0000 1.0000
1.250 0.1028 0.02007 0.00972 -0.0163 1.0000 1.0000
1.500 0.1204 0.02071 0.01032 -0.0162 1.0000 1.0000
1.750 0.1375 0.02143 0.01102 -0.0162 1.0000 1.0000
2.000 0.1818 0.02268 0.01229 -0.0213 0.9866 1.0000
2.250 0.2476 0.02407 0.01377 -0.0298 0.9605 1.0000
2.500 0.3097 0.02509 0.01491 -0.0370 0.9326 1.0000
2.750 0.3700 0.02576 0.01575 -0.0431 0.9034 1.0000
3.000 0.4300 0.02603 0.01621 -0.0484 0.8733 1.0000
3.250 0.4937 0.02581 0.01626 -0.0533 0.8426 1.0000
3.500 0.5523 0.02510 0.01579 -0.0561 0.8115 1.0000
3.750 0.5999 0.02422 0.01511 -0.0564 0.7784 1.0000
4.000 0.6376 0.02342 0.01449 -0.0550 0.7414 1.0000
4.250 0.6718 0.02265 0.01379 -0.0527 0.7014 1.0000
4.500 0.7007 0.02220 0.01331 -0.0498 0.6562 1.0000
4.750 0.7264 0.02210 0.01311 -0.0469 0.6069 1.0000
5.000 0.7497 0.02239 0.01319 -0.0441 0.5553 1.0000
5.250 0.7718 0.02299 0.01357 -0.0417 0.5039 1.0000
5.500 0.7940 0.02381 0.01414 -0.0396 0.4562 1.0000
5.750 0.8157 0.02484 0.01494 -0.0377 0.4118 1.0000
6.000 0.8370 0.02605 0.01605 -0.0361 0.3718 1.0000
6.250 0.8601 0.02735 0.01712 -0.0348 0.3377 1.0000
6.500 0.8817 0.02878 0.01855 -0.0335 0.3065 1.0000
6.750 0.9043 0.03033 0.02001 -0.0323 0.2795 1.0000
7.000 0.9246 0.03201 0.02186 -0.0310 0.2545 1.0000
7.250 0.9468 0.03392 0.02374 -0.0299 0.2336 1.0000
7.500 0.9658 0.03598 0.02606 -0.0286 0.2138 1.0000
7.750 0.9855 0.03819 0.02844 -0.0273 0.1966 1.0000
8.000 1.0041 0.04056 0.03096 -0.0260 0.1810 1.0000
8.250 1.0193 0.04326 0.03394 -0.0245 0.1674 1.0000
8.500 1.0303 0.04662 0.03771 -0.0229 0.1572 1.0000
8.750 1.0442 0.04966 0.04091 -0.0215 0.1471 1.0000
9.000 1.0472 0.05352 0.04528 -0.0197 0.1405 1.0000
9.250 1.0593 0.05728 0.04913 -0.0186 0.1345 1.0000
9.500 1.0480 0.06240 0.05481 -0.0168 0.1330 1.0000
9.750 1.0321 0.06772 0.06053 -0.0156 0.1324 1.0000
10.000 1.0128 0.07321 0.06628 -0.0149 0.1329 1.0000
10.250 0.9909 0.07866 0.07187 -0.0146 0.1338 1.0000
10.500 0.9715 0.08430 0.07757 -0.0150 0.1348 1.0000
10.750 0.9551 0.09052 0.08382 -0.0167 0.1356 1.0000
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Polar data table (+)
Polar graphs
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