SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8040 (10%) (sd8040-il) Reynolds number: 200,000 Max Cl/Cd: 65.94 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8040-il-200000-n5.txt Download as CSV file: xf-sd8040-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD8040 (10%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4516 0.07178 0.06820 -0.0410 1.0000 0.0170
-8.500 -0.4635 0.06714 0.06364 -0.0433 1.0000 0.0168
-8.250 -0.4821 0.06148 0.05803 -0.0471 1.0000 0.0167
-8.000 -0.5010 0.05541 0.05189 -0.0491 1.0000 0.0165
-7.750 -0.5196 0.05019 0.04653 -0.0486 1.0000 0.0163
-7.500 -0.5147 0.04004 0.03575 -0.0555 0.9921 0.0160
-7.250 -0.4966 0.03297 0.02792 -0.0596 0.9855 0.0160
-7.000 -0.4737 0.02853 0.02283 -0.0615 0.9798 0.0161
-6.750 -0.4459 0.02529 0.01898 -0.0630 0.9753 0.0165
-6.500 -0.4138 0.02293 0.01613 -0.0647 0.9725 0.0168
-6.250 -0.3864 0.02131 0.01423 -0.0651 0.9668 0.0172
-6.000 -0.3543 0.02037 0.01322 -0.0664 0.9629 0.0181
-5.750 -0.3206 0.01939 0.01209 -0.0679 0.9597 0.0193
-5.500 -0.2927 0.01838 0.01087 -0.0680 0.9535 0.0203
-5.250 -0.2620 0.01734 0.00972 -0.0686 0.9486 0.0210
-5.000 -0.2292 0.01650 0.00886 -0.0698 0.9448 0.0221
-4.750 -0.2034 0.01584 0.00814 -0.0694 0.9371 0.0231
-4.500 -0.1727 0.01517 0.00737 -0.0699 0.9317 0.0248
-4.250 -0.1452 0.01461 0.00681 -0.0698 0.9247 0.0271
-4.000 -0.1169 0.01411 0.00626 -0.0698 0.9176 0.0309
-3.750 -0.0885 0.01363 0.00574 -0.0698 0.9108 0.0356
-3.500 -0.0618 0.01316 0.00527 -0.0694 0.9023 0.0433
-3.250 -0.0341 0.01271 0.00487 -0.0692 0.8947 0.0579
-3.000 -0.0078 0.01229 0.00455 -0.0689 0.8855 0.0830
-2.750 0.0187 0.01185 0.00427 -0.0685 0.8764 0.1228
-2.500 0.0454 0.01144 0.00401 -0.0682 0.8672 0.1731
-2.250 0.0711 0.01102 0.00382 -0.0678 0.8565 0.2365
-2.000 0.0971 0.01058 0.00363 -0.0674 0.8465 0.3170
-1.750 0.1225 0.01015 0.00349 -0.0668 0.8352 0.4090
-1.500 0.1471 0.00975 0.00340 -0.0660 0.8230 0.5055
-1.250 0.1716 0.00941 0.00333 -0.0649 0.8105 0.5958
-1.000 0.1957 0.00915 0.00327 -0.0636 0.7975 0.6750
-0.750 0.2197 0.00896 0.00322 -0.0622 0.7839 0.7418
-0.500 0.2435 0.00884 0.00317 -0.0606 0.7692 0.7992
-0.250 0.2681 0.00875 0.00311 -0.0592 0.7539 0.8514
0.000 0.2970 0.00870 0.00304 -0.0587 0.7377 0.9007
0.250 0.3332 0.00869 0.00295 -0.0599 0.7201 0.9446
0.500 0.3748 0.00870 0.00284 -0.0625 0.7008 0.9798
0.750 0.4113 0.00875 0.00275 -0.0642 0.6808 1.0000
1.000 0.4354 0.00887 0.00272 -0.0633 0.6611 1.0000
1.250 0.4599 0.00901 0.00272 -0.0625 0.6411 1.0000
1.500 0.4846 0.00915 0.00273 -0.0618 0.6201 1.0000
1.750 0.5095 0.00932 0.00277 -0.0611 0.5989 1.0000
2.000 0.5344 0.00951 0.00282 -0.0604 0.5780 1.0000
2.250 0.5595 0.00969 0.00289 -0.0598 0.5568 1.0000
2.500 0.5846 0.00990 0.00298 -0.0592 0.5351 1.0000
2.750 0.6096 0.01012 0.00308 -0.0585 0.5138 1.0000
3.000 0.6347 0.01034 0.00321 -0.0580 0.4920 1.0000
3.250 0.6597 0.01059 0.00334 -0.0574 0.4702 1.0000
3.500 0.6845 0.01085 0.00351 -0.0568 0.4489 1.0000
3.750 0.7095 0.01112 0.00368 -0.0562 0.4272 1.0000
4.000 0.7342 0.01140 0.00387 -0.0556 0.4062 1.0000
4.250 0.7589 0.01170 0.00407 -0.0551 0.3859 1.0000
4.500 0.7836 0.01200 0.00431 -0.0545 0.3651 1.0000
4.750 0.8081 0.01232 0.00455 -0.0540 0.3454 1.0000
5.000 0.8323 0.01267 0.00482 -0.0534 0.3259 1.0000
5.250 0.8567 0.01301 0.00511 -0.0528 0.3074 1.0000
5.500 0.8809 0.01336 0.00541 -0.0522 0.2887 1.0000
5.750 0.9049 0.01373 0.00572 -0.0517 0.2709 1.0000
6.000 0.9286 0.01413 0.00608 -0.0510 0.2533 1.0000
6.250 0.9522 0.01453 0.00644 -0.0504 0.2369 1.0000
6.500 0.9755 0.01496 0.00682 -0.0498 0.2206 1.0000
6.750 0.9986 0.01541 0.00722 -0.0491 0.2051 1.0000
7.000 1.0213 0.01587 0.00766 -0.0484 0.1900 1.0000
7.250 1.0439 0.01635 0.00812 -0.0477 0.1759 1.0000
7.500 1.0661 0.01685 0.00859 -0.0469 0.1620 1.0000
7.750 1.0880 0.01737 0.00911 -0.0461 0.1490 1.0000
8.000 1.1095 0.01791 0.00964 -0.0453 0.1369 1.0000
8.250 1.1306 0.01848 0.01020 -0.0444 0.1258 1.0000
8.500 1.1509 0.01908 0.01080 -0.0434 0.1158 1.0000
8.750 1.1709 0.01970 0.01142 -0.0425 0.1062 1.0000
9.000 1.1909 0.02031 0.01207 -0.0414 0.0975 1.0000
9.250 1.2096 0.02099 0.01277 -0.0403 0.0898 1.0000
9.500 1.2275 0.02170 0.01351 -0.0391 0.0823 1.0000
9.750 1.2451 0.02241 0.01427 -0.0378 0.0758 1.0000
10.250 1.2760 0.02397 0.01592 -0.0347 0.0645 1.0000
10.500 1.2872 0.02489 0.01686 -0.0326 0.0600 1.0000
10.750 1.3001 0.02572 0.01779 -0.0308 0.0559 1.0000
11.000 1.3105 0.02670 0.01882 -0.0288 0.0523 1.0000
11.250 1.3196 0.02781 0.01999 -0.0268 0.0495 1.0000
11.500 1.3295 0.02888 0.02118 -0.0251 0.0465 1.0000
11.750 1.3370 0.03015 0.02252 -0.0232 0.0441 1.0000
12.000 1.3423 0.03163 0.02406 -0.0214 0.0422 1.0000
12.250 1.3495 0.03303 0.02561 -0.0199 0.0402 1.0000
12.500 1.3552 0.03461 0.02730 -0.0185 0.0385 1.0000
12.750 1.3586 0.03644 0.02921 -0.0173 0.0370 1.0000
13.000 1.3589 0.03865 0.03147 -0.0162 0.0358 1.0000
13.250 1.3629 0.04066 0.03366 -0.0154 0.0345 1.0000
13.500 1.3651 0.04293 0.03607 -0.0148 0.0332 1.0000
13.750 1.3658 0.04546 0.03873 -0.0144 0.0322 1.0000
14.000 1.3652 0.04826 0.04164 -0.0144 0.0313 1.0000
14.250 1.3623 0.05145 0.04493 -0.0147 0.0305 1.0000
14.500 1.3573 0.05503 0.04858 -0.0152 0.0299 1.0000
14.750 1.3556 0.05840 0.05214 -0.0159 0.0291 1.0000
15.000 1.3521 0.06213 0.05604 -0.0169 0.0283 1.0000
15.250 1.3473 0.06616 0.06023 -0.0182 0.0277 1.0000
15.500 1.3419 0.07047 0.06468 -0.0198 0.0270 1.0000
15.750 1.3354 0.07508 0.06942 -0.0217 0.0264 1.0000
16.000 1.3283 0.07992 0.07440 -0.0238 0.0260 1.0000
16.250 1.3205 0.08505 0.07965 -0.0261 0.0256 1.0000
16.500 1.3125 0.09028 0.08499 -0.0286 0.0252 1.0000
16.750 1.3043 0.09558 0.09036 -0.0311 0.0248 1.0000
17.000 1.2950 0.10145 0.09641 -0.0341 0.0244 1.0000
17.250 1.2847 0.10765 0.10279 -0.0374 0.0241 1.0000
17.500 1.2736 0.11413 0.10945 -0.0409 0.0237 1.0000
17.750 1.2620 0.12089 0.11638 -0.0448 0.0234 1.0000
18.000 1.2495 0.12804 0.12369 -0.0490 0.0230 1.0000
18.250 1.2367 0.13537 0.13118 -0.0534 0.0227 1.0000
18.500 1.2227 0.14319 0.13915 -0.0582 0.0225 1.0000
18.750 1.2070 0.15172 0.14783 -0.0636 0.0222 1.0000
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Polar data table (+)
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