LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il) Reynolds number: 200,000 Max Cl/Cd: 74.32 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l7769-il-200000-n5.txt Download as CSV file: xf-l7769-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LISSAMAN 7769 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4209 0.10679 0.10169 0.0089 0.5279 0.0463
-9.000 -0.4245 0.10270 0.09763 0.0053 0.5265 0.0466
-8.750 -0.4231 0.09882 0.09377 0.0028 0.5246 0.0466
-8.500 -0.4108 0.09379 0.08869 0.0038 0.5222 0.0392
-8.250 -0.4017 0.09099 0.08589 0.0034 0.5201 0.0384
-8.000 -0.3987 0.08752 0.08242 0.0018 0.5185 0.0377
-7.750 -0.3987 0.08382 0.07873 -0.0001 0.5170 0.0370
-7.500 -0.4031 0.08002 0.07494 -0.0024 0.5157 0.0365
-7.250 -0.4023 0.07557 0.07047 -0.0065 0.5145 0.0363
-7.000 -0.3969 0.07118 0.06602 -0.0106 0.5131 0.0366
-6.750 -0.3892 0.06629 0.06109 -0.0150 0.5115 0.0369
-6.500 -0.3800 0.06054 0.05524 -0.0198 0.5099 0.0365
-6.250 -0.3687 0.05399 0.04850 -0.0245 0.5082 0.0361
-6.000 -0.3552 0.04666 0.04087 -0.0287 0.5065 0.0359
-5.750 -0.3445 0.03488 0.02833 -0.0328 0.5054 0.0363
-5.500 -0.3278 0.02752 0.02001 -0.0340 0.5037 0.0373
-5.250 -0.3042 0.02480 0.01674 -0.0339 0.5014 0.0377
-5.000 -0.2789 0.02309 0.01463 -0.0337 0.4993 0.0381
-4.750 -0.2527 0.02182 0.01304 -0.0335 0.4974 0.0386
-4.500 -0.2259 0.02082 0.01178 -0.0332 0.4955 0.0391
-4.250 -0.1987 0.01998 0.01075 -0.0329 0.4931 0.0395
-4.000 -0.1714 0.01923 0.00987 -0.0327 0.4908 0.0400
-3.750 -0.1443 0.01860 0.00920 -0.0325 0.4886 0.0409
-3.500 -0.1168 0.01816 0.00871 -0.0323 0.4863 0.0421
-3.250 -0.0893 0.01773 0.00821 -0.0320 0.4842 0.0433
-3.000 -0.0617 0.01729 0.00767 -0.0317 0.4822 0.0444
-2.750 -0.0342 0.01689 0.00716 -0.0314 0.4804 0.0454
-2.500 -0.0064 0.01655 0.00675 -0.0312 0.4784 0.0466
-2.250 0.0214 0.01621 0.00645 -0.0310 0.4763 0.0481
-2.000 0.0493 0.01596 0.00621 -0.0308 0.4741 0.0503
-1.750 0.0772 0.01574 0.00596 -0.0306 0.4721 0.0532
-1.500 0.1051 0.01553 0.00578 -0.0304 0.4702 0.0580
-1.250 0.1329 0.01535 0.00564 -0.0301 0.4684 0.0664
-1.000 0.1609 0.01521 0.00553 -0.0299 0.4667 0.0789
-0.750 0.1889 0.01515 0.00546 -0.0297 0.4651 0.0914
-0.500 0.2169 0.01514 0.00542 -0.0295 0.4635 0.1019
-0.250 0.2452 0.01516 0.00545 -0.0294 0.4614 0.1115
0.000 0.2734 0.01521 0.00557 -0.0293 0.4593 0.1221
0.250 0.3016 0.01526 0.00566 -0.0293 0.4573 0.1332
0.500 0.3297 0.01529 0.00571 -0.0291 0.4554 0.1438
0.750 0.3576 0.01527 0.00571 -0.0290 0.4537 0.1524
1.000 0.3854 0.01523 0.00568 -0.0289 0.4521 0.1597
1.250 0.4133 0.01520 0.00566 -0.0287 0.4506 0.1682
1.500 0.4411 0.01516 0.00564 -0.0285 0.4491 0.1771
2.000 0.4967 0.01518 0.00573 -0.0283 0.4458 0.2034
2.250 0.5241 0.01512 0.00591 -0.0282 0.4439 0.2488
2.750 0.5911 0.01364 0.00628 -0.0302 0.4399 1.0000
3.000 0.6185 0.01382 0.00642 -0.0300 0.4380 1.0000
3.250 0.6459 0.01398 0.00653 -0.0298 0.4362 1.0000
3.500 0.6733 0.01414 0.00664 -0.0295 0.4346 1.0000
3.750 0.7007 0.01431 0.00678 -0.0293 0.4332 1.0000
4.000 0.7282 0.01449 0.00691 -0.0291 0.4319 1.0000
4.250 0.7554 0.01472 0.00717 -0.0290 0.4295 1.0000
4.500 0.7825 0.01492 0.00746 -0.0288 0.4258 1.0000
4.750 0.8098 0.01500 0.00754 -0.0286 0.4221 1.0000
5.000 0.8373 0.01500 0.00751 -0.0284 0.4190 1.0000
5.250 0.8649 0.01505 0.00752 -0.0281 0.4166 1.0000
5.500 0.8920 0.01525 0.00777 -0.0280 0.4140 1.0000
5.750 0.9188 0.01552 0.00815 -0.0279 0.4105 1.0000
6.000 0.9458 0.01570 0.00839 -0.0277 0.4073 1.0000
6.250 0.9731 0.01579 0.00851 -0.0275 0.4043 1.0000
6.500 1.0006 0.01572 0.00840 -0.0272 0.4009 1.0000
6.750 1.0272 0.01590 0.00872 -0.0271 0.3949 1.0000
7.000 1.0542 0.01593 0.00880 -0.0269 0.3897 1.0000
7.250 1.0815 0.01594 0.00881 -0.0267 0.3860 1.0000
7.500 1.1078 0.01620 0.00921 -0.0266 0.3812 1.0000
7.750 1.1343 0.01637 0.00948 -0.0264 0.3757 1.0000
8.000 1.1613 0.01637 0.00949 -0.0261 0.3709 1.0000
8.250 1.1871 0.01666 0.00996 -0.0260 0.3638 1.0000
8.500 1.2135 0.01677 0.01012 -0.0258 0.3576 1.0000
8.750 1.2393 0.01702 0.01051 -0.0257 0.3498 1.0000
9.000 1.2652 0.01714 0.01068 -0.0254 0.3410 1.0000
9.250 1.2903 0.01740 0.01103 -0.0252 0.3283 1.0000
9.500 1.3148 0.01769 0.01136 -0.0250 0.3109 1.0000
9.750 1.3372 0.01814 0.01173 -0.0246 0.2853 1.0000
10.000 1.3559 0.01903 0.01247 -0.0242 0.2563 1.0000
10.250 1.3714 0.02029 0.01361 -0.0237 0.2311 1.0000
10.500 1.3844 0.02175 0.01499 -0.0233 0.2117 1.0000
10.750 1.3942 0.02343 0.01663 -0.0228 0.1936 1.0000
11.000 1.4002 0.02539 0.01859 -0.0225 0.1771 1.0000
11.250 1.3974 0.02835 0.02159 -0.0232 0.1646 1.0000
11.500 1.3872 0.03191 0.02520 -0.0239 0.1561 1.0000
11.750 1.3785 0.03526 0.02855 -0.0242 0.1487 1.0000
12.000 1.3723 0.03832 0.03164 -0.0243 0.1416 1.0000
12.250 1.3661 0.04140 0.03473 -0.0244 0.1350 1.0000
12.500 1.3605 0.04445 0.03778 -0.0245 0.1278 1.0000
12.750 1.3552 0.04751 0.04086 -0.0247 0.1209 1.0000
13.000 1.3503 0.05060 0.04396 -0.0250 0.1139 1.0000
13.250 1.3463 0.05364 0.04702 -0.0253 0.1070 1.0000
13.500 1.3415 0.05684 0.05023 -0.0257 0.0998 1.0000
13.750 1.3388 0.06001 0.05342 -0.0262 0.0905 1.0000
14.000 1.3353 0.06339 0.05682 -0.0269 0.0809 1.0000
14.250 1.3296 0.06717 0.06056 -0.0278 0.0695 1.0000
14.500 1.3221 0.07129 0.06462 -0.0289 0.0580 1.0000
14.750 1.3142 0.07555 0.06882 -0.0301 0.0483 1.0000
15.000 1.3071 0.07985 0.07310 -0.0314 0.0411 1.0000
15.250 1.3008 0.08412 0.07739 -0.0326 0.0357 1.0000
15.500 1.2959 0.08831 0.08162 -0.0340 0.0326 1.0000
15.750 1.2917 0.09248 0.08586 -0.0353 0.0302 1.0000
16.250 1.2821 0.10131 0.09484 -0.0385 0.0270 1.0000
16.500 1.2780 0.10575 0.09939 -0.0401 0.0258 1.0000
16.750 1.2728 0.11042 0.10415 -0.0420 0.0249 1.0000
17.000 1.2661 0.11546 0.10927 -0.0441 0.0241 1.0000
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