CLARK Y AIRFOIL (clarky-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK Y AIRFOIL (clarky-il) Reynolds number: 100,000 Max Cl/Cd: 54.06 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarky-il-100000-n5.txt Download as CSV file: xf-clarky-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Y AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3848 0.09148 0.08634 -0.0442 1.0000 0.0488
-9.000 -0.3928 0.08770 0.08264 -0.0448 1.0000 0.0483
-8.750 -0.4052 0.08408 0.07911 -0.0450 1.0000 0.0482
-8.500 -0.4236 0.08082 0.07596 -0.0443 1.0000 0.0481
-8.250 -0.4497 0.07798 0.07325 -0.0426 1.0000 0.0478
-8.000 -0.4732 0.07408 0.06943 -0.0426 1.0000 0.0476
-7.750 -0.4772 0.06596 0.06120 -0.0504 0.9945 0.0478
-7.500 -0.4710 0.05523 0.05007 -0.0606 0.9848 0.0481
-7.250 -0.4603 0.04748 0.04178 -0.0660 0.9760 0.0481
-7.000 -0.4399 0.04156 0.03525 -0.0700 0.9701 0.0485
-6.750 -0.4209 0.03761 0.03071 -0.0714 0.9619 0.0499
-6.500 -0.3930 0.03410 0.02651 -0.0736 0.9570 0.0512
-6.250 -0.3681 0.03165 0.02352 -0.0742 0.9502 0.0518
-6.000 -0.3382 0.02958 0.02116 -0.0755 0.9450 0.0526
-5.750 -0.3038 0.02797 0.01935 -0.0775 0.9416 0.0536
-5.500 -0.2773 0.02685 0.01808 -0.0776 0.9343 0.0550
-5.250 -0.2443 0.02578 0.01681 -0.0790 0.9294 0.0572
-5.000 -0.2086 0.02460 0.01539 -0.0807 0.9259 0.0594
-4.750 -0.1829 0.02363 0.01424 -0.0803 0.9178 0.0607
-4.500 -0.1494 0.02266 0.01308 -0.0814 0.9130 0.0623
-4.250 -0.1189 0.02174 0.01218 -0.0821 0.9076 0.0643
-4.000 -0.0909 0.02113 0.01156 -0.0822 0.9003 0.0673
-3.750 -0.0572 0.02048 0.01082 -0.0832 0.8958 0.0720
-3.500 -0.0316 0.01991 0.01022 -0.0828 0.8877 0.0760
-3.250 -0.0008 0.01930 0.00960 -0.0834 0.8820 0.0818
-3.000 0.0275 0.01875 0.00904 -0.0834 0.8753 0.0904
-2.500 0.0870 0.01765 0.00812 -0.0840 0.8630 0.1349
-2.250 0.1116 0.01727 0.00790 -0.0835 0.8540 0.1735
-2.000 0.1425 0.01677 0.00763 -0.0840 0.8487 0.2392
-1.750 0.1665 0.01638 0.00756 -0.0834 0.8396 0.3217
-1.500 0.1958 0.01572 0.00732 -0.0835 0.8332 0.4281
-1.250 0.2185 0.01521 0.00725 -0.0823 0.8228 0.5479
-1.000 0.2426 0.01456 0.00714 -0.0804 0.8140 0.7134
-0.750 0.2876 0.01413 0.00700 -0.0820 0.8039 0.9044
-0.500 0.3564 0.01390 0.00661 -0.0898 0.7923 1.0000
-0.250 0.3812 0.01387 0.00641 -0.0890 0.7809 1.0000
0.000 0.4070 0.01385 0.00623 -0.0883 0.7710 1.0000
0.250 0.4303 0.01391 0.00618 -0.0874 0.7597 1.0000
0.500 0.4552 0.01395 0.00609 -0.0866 0.7493 1.0000
0.750 0.4814 0.01397 0.00597 -0.0860 0.7394 1.0000
1.000 0.5050 0.01406 0.00598 -0.0851 0.7274 1.0000
1.250 0.5297 0.01414 0.00596 -0.0843 0.7158 1.0000
1.500 0.5552 0.01420 0.00593 -0.0836 0.7046 1.0000
1.750 0.5807 0.01428 0.00592 -0.0830 0.6929 1.0000
2.000 0.6050 0.01440 0.00597 -0.0821 0.6799 1.0000
2.250 0.6296 0.01451 0.00602 -0.0813 0.6666 1.0000
2.500 0.6543 0.01463 0.00608 -0.0806 0.6528 1.0000
2.750 0.6791 0.01476 0.00614 -0.0798 0.6387 1.0000
3.000 0.7038 0.01490 0.00622 -0.0790 0.6243 1.0000
3.250 0.7283 0.01505 0.00632 -0.0782 0.6090 1.0000
3.500 0.7526 0.01522 0.00644 -0.0774 0.5927 1.0000
3.750 0.7767 0.01541 0.00657 -0.0765 0.5758 1.0000
4.000 0.8007 0.01563 0.00672 -0.0756 0.5587 1.0000
4.250 0.8246 0.01586 0.00690 -0.0748 0.5413 1.0000
4.500 0.8482 0.01613 0.00709 -0.0739 0.5236 1.0000
4.750 0.8716 0.01642 0.00731 -0.0730 0.5060 1.0000
5.000 0.8947 0.01674 0.00759 -0.0720 0.4886 1.0000
5.250 0.9177 0.01708 0.00789 -0.0711 0.4718 1.0000
5.500 0.9405 0.01745 0.00821 -0.0702 0.4556 1.0000
5.750 0.9631 0.01783 0.00856 -0.0693 0.4403 1.0000
6.000 0.9856 0.01823 0.00892 -0.0683 0.4257 1.0000
6.250 1.0075 0.01866 0.00930 -0.0673 0.4110 1.0000
6.500 1.0287 0.01910 0.00970 -0.0662 0.3953 1.0000
6.750 1.0492 0.01956 0.01013 -0.0651 0.3794 1.0000
7.000 1.0696 0.02005 0.01057 -0.0639 0.3647 1.0000
7.250 1.0904 0.02055 0.01106 -0.0628 0.3523 1.0000
7.500 1.1115 0.02103 0.01161 -0.0618 0.3409 1.0000
7.750 1.1321 0.02154 0.01216 -0.0607 0.3300 1.0000
8.000 1.1520 0.02209 0.01271 -0.0595 0.3196 1.0000
8.250 1.1715 0.02261 0.01332 -0.0583 0.3080 1.0000
8.500 1.1904 0.02315 0.01396 -0.0570 0.2964 1.0000
8.750 1.2085 0.02372 0.01460 -0.0556 0.2850 1.0000
9.000 1.2253 0.02432 0.01526 -0.0541 0.2731 1.0000
9.250 1.2410 0.02492 0.01597 -0.0524 0.2598 1.0000
9.500 1.2549 0.02556 0.01671 -0.0504 0.2452 1.0000
9.750 1.2659 0.02627 0.01747 -0.0481 0.2288 1.0000
10.000 1.2759 0.02709 0.01833 -0.0458 0.2101 1.0000
10.250 1.2839 0.02808 0.01930 -0.0434 0.1917 1.0000
10.500 1.2901 0.02926 0.02042 -0.0410 0.1750 1.0000
10.750 1.2958 0.03058 0.02170 -0.0388 0.1604 1.0000
11.000 1.3019 0.03197 0.02310 -0.0368 0.1481 1.0000
11.250 1.3080 0.03341 0.02458 -0.0349 0.1378 1.0000
11.500 1.3128 0.03500 0.02621 -0.0331 0.1293 1.0000
11.750 1.3179 0.03664 0.02791 -0.0315 0.1208 1.0000
12.000 1.3226 0.03836 0.02973 -0.0300 0.1134 1.0000
12.250 1.3252 0.04032 0.03175 -0.0286 0.1066 1.0000
12.500 1.3286 0.04230 0.03387 -0.0275 0.0989 1.0000
12.750 1.3274 0.04476 0.03636 -0.0264 0.0916 1.0000
13.000 1.3290 0.04710 0.03884 -0.0256 0.0836 1.0000
13.250 1.3278 0.04981 0.04165 -0.0250 0.0769 1.0000
13.500 1.3245 0.05284 0.04479 -0.0245 0.0696 1.0000
13.750 1.3215 0.05599 0.04807 -0.0243 0.0612 1.0000
14.000 1.3150 0.05968 0.05186 -0.0244 0.0533 1.0000
14.250 1.3059 0.06385 0.05610 -0.0248 0.0468 1.0000
14.500 1.2953 0.06844 0.06077 -0.0256 0.0416 1.0000
14.750 1.2842 0.07329 0.06572 -0.0266 0.0380 1.0000
15.000 1.2718 0.07853 0.07107 -0.0280 0.0354 1.0000
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Polar data table (+)
Polar graphs
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