SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8040 (10%) (sd8040-il) Reynolds number: 200,000 Max Cl/Cd: 69.17 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8040-il-200000.txt Download as CSV file: xf-sd8040-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3075 0.08063 0.07731 -0.0332 1.0000 0.0582
-8.500 -0.3082 0.07704 0.07376 -0.0340 1.0000 0.0599
-8.250 -0.3984 0.08239 0.07893 -0.0353 1.0000 0.0565
-8.000 -0.3968 0.07992 0.07650 -0.0350 1.0000 0.0580
-7.750 -0.4045 0.07712 0.07379 -0.0351 1.0000 0.0589
-7.500 -0.4195 0.07450 0.07126 -0.0347 1.0000 0.0599
-7.250 -0.4337 0.07127 0.06808 -0.0356 1.0000 0.0606
-7.000 -0.4503 0.06734 0.06415 -0.0371 1.0000 0.0622
-6.750 -0.4829 0.06237 0.05864 -0.0416 1.0000 0.0645
-6.500 -0.4816 0.05703 0.05347 -0.0402 1.0000 0.0657
-6.250 -0.4754 0.05503 0.05155 -0.0381 1.0000 0.0666
-6.000 -0.4698 0.05302 0.04954 -0.0364 1.0000 0.0679
-5.750 -0.4417 0.04933 0.04571 -0.0403 0.9961 0.0719
-5.250 -0.3782 0.02728 0.02088 -0.0494 0.9859 0.0377
-5.000 -0.3439 0.02446 0.01773 -0.0512 0.9819 0.0371
-4.750 -0.3079 0.02263 0.01545 -0.0528 0.9769 0.0375
-4.500 -0.2704 0.02058 0.01334 -0.0553 0.9736 0.0399
-4.250 -0.2358 0.01931 0.01193 -0.0565 0.9680 0.0413
-4.000 -0.1979 0.01811 0.01057 -0.0583 0.9633 0.0432
-3.750 -0.1569 0.01683 0.00921 -0.0607 0.9600 0.0463
-3.500 -0.1240 0.01616 0.00858 -0.0617 0.9528 0.0524
-3.250 -0.0844 0.01520 0.00768 -0.0639 0.9481 0.0618
-3.000 -0.0403 0.01425 0.00683 -0.0671 0.9451 0.0889
-2.750 -0.0106 0.01332 0.00629 -0.0677 0.9364 0.1552
-2.500 0.0275 0.01231 0.00594 -0.0701 0.9316 0.3033
-2.250 0.0558 0.01157 0.00579 -0.0702 0.9232 0.4594
-2.000 0.0864 0.01091 0.00569 -0.0702 0.9165 0.6102
-1.750 0.1112 0.01052 0.00565 -0.0687 0.9074 0.7191
-1.500 0.1381 0.01019 0.00553 -0.0672 0.8999 0.8045
-1.250 0.1612 0.01001 0.00545 -0.0649 0.8896 0.8708
-1.000 0.1975 0.00980 0.00521 -0.0652 0.8829 0.9273
-0.750 0.2458 0.00964 0.00497 -0.0685 0.8737 0.9656
-0.500 0.3028 0.00938 0.00458 -0.0738 0.8666 0.9899
-0.250 0.3390 0.00922 0.00433 -0.0753 0.8534 1.0000
0.000 0.3590 0.00914 0.00414 -0.0736 0.8388 1.0000
0.250 0.3804 0.00908 0.00397 -0.0720 0.8238 1.0000
0.500 0.4028 0.00904 0.00383 -0.0706 0.8082 1.0000
0.750 0.4260 0.00903 0.00370 -0.0693 0.7921 1.0000
1.000 0.4498 0.00904 0.00360 -0.0681 0.7752 1.0000
1.250 0.4742 0.00907 0.00351 -0.0671 0.7575 1.0000
1.500 0.4990 0.00912 0.00344 -0.0661 0.7393 1.0000
1.750 0.5236 0.00921 0.00344 -0.0652 0.7190 1.0000
2.000 0.5486 0.00932 0.00344 -0.0643 0.6983 1.0000
2.250 0.5737 0.00945 0.00345 -0.0635 0.6777 1.0000
2.500 0.5987 0.00961 0.00350 -0.0627 0.6559 1.0000
2.750 0.6237 0.00978 0.00357 -0.0619 0.6332 1.0000
3.000 0.6487 0.00998 0.00364 -0.0611 0.6109 1.0000
3.250 0.6736 0.01019 0.00375 -0.0604 0.5872 1.0000
3.500 0.6983 0.01044 0.00387 -0.0596 0.5641 1.0000
3.750 0.7231 0.01067 0.00403 -0.0589 0.5397 1.0000
4.000 0.7475 0.01096 0.00419 -0.0581 0.5162 1.0000
4.250 0.7720 0.01123 0.00438 -0.0574 0.4917 1.0000
4.500 0.7962 0.01155 0.00460 -0.0567 0.4682 1.0000
4.750 0.8204 0.01186 0.00483 -0.0560 0.4441 1.0000
5.000 0.8443 0.01222 0.00508 -0.0552 0.4213 1.0000
5.250 0.8682 0.01256 0.00536 -0.0545 0.3977 1.0000
5.500 0.8916 0.01297 0.00567 -0.0537 0.3757 1.0000
5.750 0.9153 0.01334 0.00599 -0.0530 0.3530 1.0000
6.000 0.9384 0.01376 0.00634 -0.0523 0.3314 1.0000
6.250 0.9613 0.01421 0.00672 -0.0515 0.3106 1.0000
6.500 0.9842 0.01465 0.00712 -0.0507 0.2897 1.0000
6.750 1.0065 0.01515 0.00754 -0.0499 0.2698 1.0000
7.000 1.0283 0.01569 0.00801 -0.0490 0.2512 1.0000
7.250 1.0505 0.01619 0.00849 -0.0482 0.2321 1.0000
7.500 1.0720 0.01674 0.00901 -0.0473 0.2143 1.0000
7.750 1.0930 0.01732 0.00955 -0.0463 0.1975 1.0000
8.000 1.1136 0.01794 0.01014 -0.0453 0.1819 1.0000
8.250 1.1337 0.01859 0.01077 -0.0443 0.1674 1.0000
8.500 1.1534 0.01927 0.01143 -0.0432 0.1539 1.0000
8.750 1.1724 0.01999 0.01216 -0.0420 0.1414 1.0000
9.000 1.1905 0.02078 0.01293 -0.0408 0.1300 1.0000
9.250 1.2074 0.02165 0.01375 -0.0394 0.1195 1.0000
9.500 1.2240 0.02247 0.01458 -0.0379 0.1097 1.0000
9.750 1.2405 0.02331 0.01550 -0.0365 0.1006 1.0000
10.000 1.2542 0.02439 0.01656 -0.0347 0.0930 1.0000
10.250 1.2675 0.02527 0.01749 -0.0329 0.0861 1.0000
10.500 1.2787 0.02643 0.01869 -0.0308 0.0801 1.0000
10.750 1.2898 0.02741 0.01973 -0.0287 0.0750 1.0000
11.000 1.2996 0.02885 0.02117 -0.0267 0.0705 1.0000
11.250 1.3103 0.02992 0.02237 -0.0248 0.0664 1.0000
11.500 1.3192 0.03128 0.02371 -0.0230 0.0629 1.0000
11.750 1.3296 0.03289 0.02543 -0.0214 0.0600 1.0000
12.000 1.3384 0.03425 0.02694 -0.0197 0.0571 1.0000
12.250 1.3466 0.03566 0.02839 -0.0182 0.0545 1.0000
12.500 1.3573 0.03776 0.03048 -0.0170 0.0520 1.0000
12.750 1.3626 0.03944 0.03240 -0.0154 0.0503 1.0000
13.000 1.3680 0.04129 0.03441 -0.0140 0.0484 1.0000
13.250 1.3734 0.04315 0.03638 -0.0128 0.0468 1.0000
13.500 1.3802 0.04505 0.03827 -0.0120 0.0451 1.0000
13.750 1.3855 0.04785 0.04121 -0.0110 0.0436 1.0000
14.000 1.3827 0.05048 0.04411 -0.0101 0.0426 1.0000
14.250 1.3800 0.05341 0.04727 -0.0096 0.0417 1.0000
14.500 1.3765 0.05653 0.05059 -0.0093 0.0408 1.0000
14.750 1.3719 0.05986 0.05410 -0.0094 0.0399 1.0000
15.000 1.3674 0.06329 0.05769 -0.0097 0.0391 1.0000
15.250 1.3665 0.06637 0.06083 -0.0102 0.0381 1.0000
15.500 1.3667 0.06981 0.06432 -0.0106 0.0372 1.0000
15.750 1.3539 0.07515 0.06985 -0.0119 0.0367 1.0000
16.000 1.3355 0.08087 0.07583 -0.0143 0.0365 1.0000
16.250 1.3155 0.08729 0.08250 -0.0176 0.0363 1.0000
16.500 1.2940 0.09451 0.08997 -0.0215 0.0363 1.0000
16.750 1.2700 0.10269 0.09837 -0.0264 0.0363 1.0000
17.000 1.2435 0.11192 0.10784 -0.0323 0.0363 1.0000
17.250 1.2145 0.12234 0.11845 -0.0391 0.0365 1.0000
17.500 1.1812 0.13453 0.13085 -0.0474 0.0368 1.0000
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