CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 50,000 Max Cl/Cd: 31.71 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkys-il-50000-n5.txt Download as CSV file: xf-clarkys-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YS AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5270 0.09189 0.08532 -0.0216 1.0000 0.0742
-9.500 -0.5260 0.08754 0.08099 -0.0233 1.0000 0.0736
-9.250 -0.5302 0.08292 0.07640 -0.0251 1.0000 0.0731
-9.000 -0.5375 0.07848 0.07196 -0.0264 1.0000 0.0725
-8.750 -0.5474 0.07426 0.06772 -0.0267 1.0000 0.0721
-8.500 -0.5568 0.06996 0.06335 -0.0269 1.0000 0.0718
-8.250 -0.5651 0.06576 0.05902 -0.0265 1.0000 0.0718
-8.000 -0.5729 0.06177 0.05483 -0.0255 1.0000 0.0722
-7.750 -0.5804 0.05816 0.05097 -0.0237 1.0000 0.0727
-7.500 -0.5885 0.05526 0.04781 -0.0206 1.0000 0.0732
-7.250 -0.5981 0.05302 0.04531 -0.0165 0.9978 0.0735
-7.000 -0.5837 0.04922 0.04100 -0.0169 0.9792 0.0738
-6.750 -0.5647 0.04574 0.03698 -0.0173 0.9663 0.0741
-6.500 -0.5428 0.04265 0.03343 -0.0176 0.9555 0.0747
-6.250 -0.5165 0.04003 0.03051 -0.0185 0.9464 0.0758
-6.000 -0.4909 0.03821 0.02848 -0.0190 0.9367 0.0781
-5.750 -0.4627 0.03646 0.02643 -0.0197 0.9284 0.0811
-5.500 -0.4359 0.03468 0.02426 -0.0198 0.9196 0.0838
-5.250 -0.4054 0.03287 0.02203 -0.0203 0.9119 0.0858
-5.000 -0.3739 0.03133 0.02007 -0.0209 0.9040 0.0879
-4.750 -0.3387 0.02985 0.01846 -0.0223 0.8974 0.0909
-4.500 -0.3066 0.02881 0.01734 -0.0232 0.8895 0.0958
-4.250 -0.2677 0.02779 0.01607 -0.0250 0.8834 0.1039
-4.000 -0.2290 0.02682 0.01510 -0.0271 0.8760 0.1131
-3.750 -0.1867 0.02582 0.01405 -0.0295 0.8699 0.1264
-3.500 -0.1525 0.02506 0.01335 -0.0307 0.8622 0.1509
-3.250 -0.1196 0.02430 0.01284 -0.0317 0.8552 0.1958
-3.000 -0.0926 0.02354 0.01262 -0.0319 0.8471 0.2811
-2.750 0.0176 0.02203 0.01339 -0.0437 0.8458 0.8621
-2.500 0.0543 0.02300 0.01398 -0.0439 0.8388 0.9443
-2.250 0.1586 0.02231 0.01277 -0.0586 0.8321 1.0000
-2.000 0.1799 0.02249 0.01271 -0.0574 0.8207 1.0000
-1.750 0.2004 0.02267 0.01267 -0.0558 0.8082 1.0000
-1.500 0.2207 0.02285 0.01266 -0.0542 0.7953 1.0000
-1.250 0.2416 0.02302 0.01266 -0.0528 0.7821 1.0000
-1.000 0.2628 0.02318 0.01269 -0.0515 0.7694 1.0000
-0.750 0.2847 0.02335 0.01274 -0.0505 0.7577 1.0000
-0.500 0.3066 0.02351 0.01279 -0.0493 0.7469 1.0000
-0.250 0.3283 0.02363 0.01280 -0.0479 0.7369 1.0000
0.000 0.3505 0.02379 0.01290 -0.0470 0.7248 1.0000
0.250 0.3729 0.02394 0.01299 -0.0461 0.7131 1.0000
0.500 0.3952 0.02404 0.01303 -0.0450 0.7023 1.0000
0.750 0.4171 0.02408 0.01301 -0.0436 0.6917 1.0000
1.000 0.4393 0.02421 0.01311 -0.0426 0.6790 1.0000
1.250 0.4614 0.02431 0.01318 -0.0414 0.6670 1.0000
1.500 0.4834 0.02434 0.01318 -0.0400 0.6559 1.0000
1.750 0.5054 0.02432 0.01312 -0.0385 0.6448 1.0000
2.000 0.5274 0.02444 0.01324 -0.0374 0.6316 1.0000
2.250 0.5494 0.02454 0.01334 -0.0362 0.6189 1.0000
2.500 0.5715 0.02460 0.01339 -0.0348 0.6067 1.0000
2.750 0.5936 0.02458 0.01333 -0.0333 0.5957 1.0000
3.000 0.6156 0.02471 0.01348 -0.0320 0.5826 1.0000
3.250 0.6376 0.02492 0.01370 -0.0309 0.5693 1.0000
3.500 0.6594 0.02511 0.01391 -0.0297 0.5564 1.0000
3.750 0.6814 0.02529 0.01409 -0.0284 0.5445 1.0000
4.000 0.7037 0.02537 0.01416 -0.0270 0.5340 1.0000
4.250 0.7251 0.02576 0.01460 -0.0260 0.5210 1.0000
4.500 0.7464 0.02613 0.01502 -0.0249 0.5089 1.0000
4.750 0.7680 0.02643 0.01535 -0.0236 0.4982 1.0000
5.000 0.7897 0.02668 0.01562 -0.0224 0.4877 1.0000
5.250 0.8100 0.02716 0.01618 -0.0212 0.4754 1.0000
5.500 0.8303 0.02757 0.01667 -0.0200 0.4638 1.0000
5.750 0.8513 0.02785 0.01697 -0.0186 0.4528 1.0000
6.000 0.8715 0.02821 0.01737 -0.0172 0.4413 1.0000
6.250 0.8902 0.02876 0.01802 -0.0158 0.4290 1.0000
6.500 0.9091 0.02923 0.01860 -0.0144 0.4172 1.0000
6.750 0.9283 0.02960 0.01901 -0.0129 0.4053 1.0000
7.000 0.9474 0.02991 0.01932 -0.0112 0.3927 1.0000
7.250 0.9641 0.03040 0.01989 -0.0095 0.3788 1.0000
7.500 0.9794 0.03100 0.02060 -0.0077 0.3648 1.0000
7.750 0.9940 0.03163 0.02132 -0.0058 0.3510 1.0000
8.000 1.0080 0.03229 0.02207 -0.0039 0.3377 1.0000
8.250 1.0217 0.03297 0.02282 -0.0018 0.3247 1.0000
8.500 1.0352 0.03361 0.02352 0.0002 0.3120 1.0000
8.750 1.0464 0.03438 0.02440 0.0025 0.2991 1.0000
9.000 1.0529 0.03542 0.02561 0.0051 0.2861 1.0000
9.250 1.0584 0.03644 0.02676 0.0078 0.2735 1.0000
9.500 1.0629 0.03743 0.02784 0.0106 0.2614 1.0000
9.750 1.0675 0.03835 0.02878 0.0135 0.2502 1.0000
10.000 1.0668 0.03957 0.03012 0.0167 0.2395 1.0000
10.250 1.0641 0.04090 0.03155 0.0201 0.2299 1.0000
10.500 1.0658 0.04179 0.03243 0.0233 0.2219 1.0000
10.750 1.0558 0.04352 0.03431 0.0268 0.2142 1.0000
11.000 1.0581 0.04462 0.03538 0.0294 0.2068 1.0000
11.250 1.0500 0.04665 0.03756 0.0319 0.1995 1.0000
11.500 1.0556 0.04776 0.03863 0.0340 0.1928 1.0000
11.750 1.0468 0.05027 0.04131 0.0359 0.1864 1.0000
12.000 1.0552 0.05136 0.04238 0.0376 0.1801 1.0000
12.250 1.0451 0.05428 0.04546 0.0389 0.1746 1.0000
12.500 1.0419 0.05640 0.04764 0.0402 0.1680 1.0000
12.750 1.0371 0.05885 0.05014 0.0411 0.1619 1.0000
13.000 1.0231 0.06257 0.05402 0.0414 0.1565 1.0000
13.250 1.0240 0.06424 0.05564 0.0422 0.1487 1.0000
13.500 1.0025 0.06947 0.06110 0.0414 0.1445 1.0000
13.750 1.0092 0.07034 0.06183 0.0423 0.1357 1.0000
14.000 0.9833 0.07686 0.06862 0.0404 0.1328 1.0000
14.250 0.9528 0.08469 0.07665 0.0375 0.1303 1.0000
14.750 0.9250 0.09501 0.08708 0.0340 0.1190 1.0000
15.000 0.8728 0.10953 0.10165 0.0274 0.1198 1.0000
15.250 0.8166 0.12696 0.11898 0.0194 0.1201 1.0000
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Polar data table (+)
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