SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SD8000-089-88 (sd8000-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.59 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8000-il-1000000-n5.txt Download as CSV file: xf-sd8000-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8567 0.08434 0.08219 -0.0240 1.0000 0.0039
-13.750 -0.9560 0.06247 0.06019 -0.0378 1.0000 0.0038
-13.500 -1.0408 0.03923 0.03654 -0.0576 1.0000 0.0036
-13.250 -1.0672 0.03437 0.03149 -0.0597 1.0000 0.0036
-13.000 -1.0740 0.03198 0.02894 -0.0582 1.0000 0.0036
-12.750 -1.0710 0.02974 0.02653 -0.0575 1.0000 0.0036
-12.500 -1.0628 0.02779 0.02441 -0.0567 1.0000 0.0037
-12.250 -1.0503 0.02620 0.02266 -0.0561 1.0000 0.0037
-12.000 -1.0358 0.02471 0.02102 -0.0554 1.0000 0.0038
-11.750 -1.0191 0.02342 0.01959 -0.0547 1.0000 0.0039
-11.500 -1.0014 0.02222 0.01825 -0.0541 1.0000 0.0039
-11.250 -0.9821 0.02123 0.01713 -0.0534 1.0000 0.0040
-11.000 -0.9628 0.02020 0.01597 -0.0527 1.0000 0.0040
-10.750 -0.9425 0.01936 0.01503 -0.0520 1.0000 0.0041
-10.500 -0.9224 0.01857 0.01414 -0.0511 1.0000 0.0041
-10.250 -0.9052 0.01744 0.01287 -0.0499 1.0000 0.0043
-10.000 -0.8826 0.01650 0.01181 -0.0495 0.9989 0.0044
-9.750 -0.8538 0.01565 0.01085 -0.0504 0.9962 0.0047
-9.500 -0.8241 0.01494 0.01005 -0.0513 0.9939 0.0048
-9.250 -0.7952 0.01430 0.00933 -0.0519 0.9911 0.0050
-9.000 -0.7656 0.01373 0.00868 -0.0527 0.9884 0.0053
-8.750 -0.7352 0.01320 0.00808 -0.0535 0.9859 0.0055
-8.500 -0.7043 0.01269 0.00750 -0.0544 0.9838 0.0058
-8.250 -0.6760 0.01225 0.00700 -0.0547 0.9797 0.0061
-8.000 -0.6472 0.01181 0.00649 -0.0551 0.9756 0.0065
-7.750 -0.6181 0.01134 0.00598 -0.0556 0.9719 0.0072
-7.500 -0.5908 0.01096 0.00557 -0.0556 0.9673 0.0080
-7.250 -0.5638 0.01063 0.00520 -0.0554 0.9620 0.0087
-7.000 -0.5368 0.01029 0.00482 -0.0553 0.9572 0.0100
-6.750 -0.5107 0.00999 0.00449 -0.0549 0.9515 0.0117
-6.500 -0.4844 0.00970 0.00419 -0.0546 0.9459 0.0136
-6.250 -0.4580 0.00945 0.00391 -0.0542 0.9409 0.0156
-6.000 -0.4314 0.00920 0.00364 -0.0540 0.9350 0.0177
-5.750 -0.4050 0.00897 0.00339 -0.0536 0.9294 0.0204
-5.500 -0.3782 0.00873 0.00315 -0.0533 0.9236 0.0236
-5.250 -0.3515 0.00853 0.00293 -0.0530 0.9169 0.0267
-5.000 -0.3246 0.00833 0.00272 -0.0527 0.9106 0.0307
-4.750 -0.2975 0.00814 0.00252 -0.0525 0.9035 0.0353
-4.500 -0.2706 0.00794 0.00234 -0.0523 0.8969 0.0431
-4.250 -0.2432 0.00777 0.00217 -0.0521 0.8892 0.0490
-4.000 -0.2159 0.00762 0.00200 -0.0518 0.8815 0.0548
-3.750 -0.1885 0.00747 0.00185 -0.0517 0.8724 0.0616
-3.500 -0.1610 0.00734 0.00171 -0.0515 0.8629 0.0693
-3.250 -0.1337 0.00721 0.00158 -0.0512 0.8524 0.0793
-3.000 -0.1063 0.00707 0.00145 -0.0511 0.8403 0.0919
-2.750 -0.0788 0.00695 0.00133 -0.0509 0.8271 0.1068
-2.500 -0.0514 0.00684 0.00123 -0.0507 0.8126 0.1213
-2.250 -0.0240 0.00673 0.00112 -0.0505 0.7970 0.1413
-2.000 0.0033 0.00663 0.00104 -0.0503 0.7802 0.1624
-1.750 0.0307 0.00653 0.00096 -0.0501 0.7612 0.1897
-1.500 0.0579 0.00646 0.00089 -0.0499 0.7387 0.2156
-1.250 0.0850 0.00642 0.00084 -0.0497 0.7137 0.2436
-1.000 0.1120 0.00635 0.00080 -0.0495 0.6889 0.2823
-0.750 0.1391 0.00628 0.00077 -0.0494 0.6639 0.3245
-0.500 0.1662 0.00622 0.00075 -0.0492 0.6378 0.3692
-0.250 0.1932 0.00617 0.00075 -0.0491 0.6107 0.4155
0.000 0.2201 0.00615 0.00076 -0.0489 0.5807 0.4627
0.500 0.2738 0.00617 0.00082 -0.0485 0.5194 0.5539
0.750 0.3006 0.00619 0.00087 -0.0483 0.4897 0.6011
1.000 0.3273 0.00623 0.00093 -0.0481 0.4598 0.6448
1.250 0.3539 0.00629 0.00100 -0.0478 0.4295 0.6871
1.500 0.3802 0.00637 0.00108 -0.0475 0.3981 0.7291
1.750 0.4063 0.00646 0.00118 -0.0471 0.3672 0.7703
2.000 0.4323 0.00655 0.00128 -0.0467 0.3389 0.8076
2.250 0.4579 0.00665 0.00138 -0.0461 0.3123 0.8422
2.500 0.4829 0.00672 0.00148 -0.0454 0.2918 0.8796
2.750 0.5065 0.00681 0.00160 -0.0443 0.2684 0.9213
3.000 0.5352 0.00695 0.00170 -0.0443 0.2453 0.9634
3.250 0.5719 0.00715 0.00181 -0.0463 0.2233 0.9971
3.500 0.5990 0.00737 0.00194 -0.0462 0.2025 1.0000
3.750 0.6255 0.00760 0.00208 -0.0460 0.1833 1.0000
4.000 0.6520 0.00784 0.00223 -0.0457 0.1655 1.0000
4.250 0.6785 0.00807 0.00240 -0.0455 0.1493 1.0000
4.500 0.7050 0.00830 0.00256 -0.0452 0.1353 1.0000
4.750 0.7316 0.00853 0.00274 -0.0450 0.1236 1.0000
5.000 0.7582 0.00875 0.00292 -0.0448 0.1130 1.0000
5.250 0.7844 0.00901 0.00313 -0.0445 0.1002 1.0000
5.500 0.8104 0.00932 0.00335 -0.0442 0.0859 1.0000
5.750 0.8364 0.00961 0.00358 -0.0439 0.0741 1.0000
6.000 0.8625 0.00987 0.00382 -0.0437 0.0661 1.0000
6.250 0.8884 0.01017 0.00408 -0.0434 0.0581 1.0000
6.500 0.9144 0.01044 0.00433 -0.0431 0.0516 1.0000
6.750 0.9402 0.01074 0.00461 -0.0427 0.0456 1.0000
7.000 0.9655 0.01109 0.00492 -0.0424 0.0388 1.0000
7.250 0.9910 0.01141 0.00523 -0.0420 0.0335 1.0000
7.500 1.0161 0.01177 0.00557 -0.0416 0.0284 1.0000
7.750 1.0409 0.01216 0.00594 -0.0412 0.0235 1.0000
8.000 1.0657 0.01254 0.00631 -0.0408 0.0198 1.0000
8.250 1.0901 0.01296 0.00674 -0.0403 0.0167 1.0000
8.500 1.1146 0.01335 0.00714 -0.0398 0.0151 1.0000
8.750 1.1386 0.01380 0.00761 -0.0392 0.0134 1.0000
9.000 1.1626 0.01424 0.00807 -0.0387 0.0124 1.0000
9.250 1.1866 0.01464 0.00852 -0.0382 0.0118 1.0000
9.500 1.2101 0.01510 0.00902 -0.0376 0.0112 1.0000
9.750 1.2331 0.01558 0.00954 -0.0369 0.0107 1.0000
10.000 1.2556 0.01612 0.01012 -0.0362 0.0101 1.0000
10.250 1.2771 0.01674 0.01080 -0.0354 0.0095 1.0000
10.500 1.2990 0.01729 0.01140 -0.0346 0.0092 1.0000
10.750 1.3210 0.01779 0.01196 -0.0339 0.0089 1.0000
11.000 1.3423 0.01835 0.01259 -0.0330 0.0086 1.0000
11.250 1.3630 0.01893 0.01323 -0.0321 0.0083 1.0000
11.500 1.3832 0.01951 0.01387 -0.0312 0.0080 1.0000
11.750 1.4025 0.02015 0.01457 -0.0302 0.0077 1.0000
12.000 1.4208 0.02085 0.01532 -0.0290 0.0074 1.0000
12.250 1.4374 0.02164 0.01618 -0.0276 0.0071 1.0000
12.500 1.4512 0.02259 0.01724 -0.0259 0.0068 1.0000
12.750 1.4646 0.02346 0.01819 -0.0242 0.0066 1.0000
13.000 1.4772 0.02415 0.01895 -0.0221 0.0065 1.0000
13.250 1.4874 0.02492 0.01981 -0.0199 0.0063 1.0000
13.500 1.4954 0.02585 0.02083 -0.0175 0.0062 1.0000
13.750 1.5037 0.02681 0.02187 -0.0154 0.0061 1.0000
14.000 1.5116 0.02784 0.02299 -0.0134 0.0059 1.0000
14.250 1.5186 0.02899 0.02422 -0.0116 0.0057 1.0000
14.500 1.5249 0.03025 0.02556 -0.0099 0.0055 1.0000
14.750 1.5277 0.03185 0.02727 -0.0082 0.0054 1.0000
15.000 1.5312 0.03352 0.02903 -0.0069 0.0052 1.0000
15.250 1.5322 0.03551 0.03112 -0.0058 0.0051 1.0000
15.500 1.5314 0.03785 0.03355 -0.0050 0.0050 1.0000
15.750 1.5293 0.04050 0.03630 -0.0047 0.0048 1.0000
16.000 1.5231 0.04385 0.03978 -0.0049 0.0048 1.0000
16.250 1.5145 0.04780 0.04387 -0.0058 0.0047 1.0000
16.500 1.5013 0.05279 0.04901 -0.0076 0.0046 1.0000
16.750 1.4844 0.05884 0.05521 -0.0104 0.0046 1.0000
17.000 1.4724 0.06453 0.06105 -0.0134 0.0045 1.0000
17.250 1.4464 0.07313 0.06982 -0.0183 0.0046 1.0000
17.750 1.3821 0.09415 0.09121 -0.0306 0.0046 1.0000
18.000 1.3476 0.10564 0.10287 -0.0373 0.0047 1.0000
18.250 1.3119 0.11769 0.11509 -0.0443 0.0048 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SD8000-089-88 (sd8000-il)