CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 100,000 Max Cl/Cd: 47.7 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkyh-il-100000.txt Download as CSV file: xf-clarkyh-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YH 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3851 0.11209 0.10735 -0.0174 1.0000 0.1435
-11.500 -0.3650 0.10763 0.10288 -0.0160 1.0000 0.1471
-11.250 -0.4958 0.11188 0.10691 -0.0084 1.0000 0.1431
-11.000 -0.4974 0.10725 0.10233 -0.0105 1.0000 0.1455
-10.750 -0.4737 0.10445 0.09948 -0.0078 1.0000 0.1515
-10.500 -0.5101 0.10067 0.09585 -0.0173 1.0000 0.1576
-10.250 -0.4755 0.09687 0.09199 -0.0118 1.0000 0.1618
-10.000 -0.4722 0.09371 0.08886 -0.0132 1.0000 0.1686
-9.750 -0.5042 0.08847 0.08376 -0.0217 1.0000 0.1733
-9.500 -0.4690 0.08617 0.08140 -0.0162 1.0000 0.1785
-9.250 -0.5313 0.08182 0.07709 -0.0290 1.0000 0.1870
-9.000 -0.5981 0.05761 0.05205 -0.0381 1.0000 0.1159
-8.750 -0.5840 0.05446 0.04903 -0.0364 1.0000 0.1144
-8.500 -0.5881 0.05123 0.04573 -0.0334 1.0000 0.1131
-8.250 -0.5955 0.04777 0.04207 -0.0300 1.0000 0.1114
-8.000 -0.6046 0.04350 0.03744 -0.0264 1.0000 0.1089
-7.750 -0.6110 0.03876 0.03212 -0.0228 1.0000 0.1062
-7.500 -0.6046 0.03637 0.02944 -0.0201 1.0000 0.1075
-7.250 -0.5956 0.03422 0.02697 -0.0177 1.0000 0.1094
-7.000 -0.5845 0.03201 0.02435 -0.0154 1.0000 0.1107
-6.750 -0.5707 0.03010 0.02204 -0.0135 1.0000 0.1122
-6.500 -0.5554 0.02869 0.02020 -0.0117 1.0000 0.1147
-6.250 -0.5145 0.02655 0.01773 -0.0146 0.9940 0.1178
-6.000 -0.4681 0.02512 0.01618 -0.0184 0.9855 0.1225
-5.750 -0.4232 0.02394 0.01475 -0.0217 0.9772 0.1282
-5.500 -0.3751 0.02262 0.01335 -0.0255 0.9702 0.1333
-5.250 -0.3328 0.02183 0.01257 -0.0283 0.9604 0.1414
-5.000 -0.2865 0.02110 0.01192 -0.0318 0.9523 0.1519
-4.750 -0.2412 0.02050 0.01139 -0.0350 0.9432 0.1675
-4.500 -0.1994 0.02007 0.01102 -0.0374 0.9330 0.2018
-4.250 -0.1565 0.01921 0.01042 -0.0401 0.9250 0.2657
-4.000 -0.1249 0.01870 0.01010 -0.0407 0.9123 0.3064
-3.750 -0.0928 0.01837 0.00986 -0.0412 0.9002 0.3385
-3.500 -0.0594 0.01802 0.00963 -0.0418 0.8899 0.3714
-3.250 -0.0297 0.01768 0.00942 -0.0417 0.8781 0.4028
-3.000 -0.0039 0.01732 0.00927 -0.0409 0.8648 0.4408
-2.750 0.0201 0.01664 0.00910 -0.0396 0.8524 0.5299
-2.500 0.1786 0.01610 0.00959 -0.0601 0.8532 0.9866
-2.250 0.2267 0.01593 0.00921 -0.0637 0.8405 1.0000
-2.000 0.2475 0.01595 0.00907 -0.0620 0.8259 1.0000
-1.750 0.2686 0.01595 0.00892 -0.0603 0.8117 1.0000
-1.500 0.2903 0.01597 0.00881 -0.0589 0.7964 1.0000
-1.250 0.3122 0.01596 0.00869 -0.0575 0.7813 1.0000
-1.000 0.3343 0.01595 0.00857 -0.0562 0.7665 1.0000
-0.750 0.3568 0.01594 0.00845 -0.0549 0.7522 1.0000
-0.500 0.3796 0.01594 0.00836 -0.0538 0.7392 1.0000
-0.250 0.4027 0.01593 0.00824 -0.0526 0.7280 1.0000
0.000 0.4262 0.01596 0.00819 -0.0516 0.7161 1.0000
0.250 0.4498 0.01605 0.00822 -0.0508 0.7038 1.0000
0.500 0.4735 0.01613 0.00823 -0.0499 0.6931 1.0000
0.750 0.4974 0.01616 0.00817 -0.0489 0.6835 1.0000
1.000 0.5211 0.01633 0.00831 -0.0482 0.6718 1.0000
1.250 0.5450 0.01648 0.00841 -0.0474 0.6620 1.0000
1.500 0.5692 0.01664 0.00851 -0.0467 0.6530 1.0000
1.750 0.5928 0.01688 0.00876 -0.0460 0.6425 1.0000
2.000 0.6170 0.01700 0.00880 -0.0451 0.6331 1.0000
2.250 0.6402 0.01722 0.00903 -0.0443 0.6216 1.0000
2.500 0.6635 0.01746 0.00926 -0.0434 0.6107 1.0000
2.750 0.6881 0.01762 0.00936 -0.0426 0.6017 1.0000
3.000 0.7106 0.01793 0.00976 -0.0419 0.5904 1.0000
3.250 0.7341 0.01818 0.01001 -0.0411 0.5802 1.0000
3.500 0.7580 0.01834 0.01017 -0.0402 0.5696 1.0000
3.750 0.7803 0.01859 0.01049 -0.0393 0.5568 1.0000
4.000 0.8029 0.01876 0.01070 -0.0382 0.5433 1.0000
4.250 0.8255 0.01884 0.01081 -0.0371 0.5281 1.0000
4.500 0.8478 0.01887 0.01084 -0.0359 0.5106 1.0000
4.750 0.8700 0.01887 0.01081 -0.0346 0.4913 1.0000
5.000 0.8918 0.01896 0.01084 -0.0333 0.4706 1.0000
5.250 0.9121 0.01922 0.01110 -0.0319 0.4469 1.0000
5.500 0.9334 0.01957 0.01134 -0.0307 0.4256 1.0000
5.750 0.9537 0.02004 0.01178 -0.0295 0.4049 1.0000
6.000 0.9738 0.02052 0.01227 -0.0283 0.3861 1.0000
6.250 0.9943 0.02099 0.01276 -0.0272 0.3704 1.0000
6.500 1.0149 0.02145 0.01323 -0.0262 0.3565 1.0000
6.750 1.0339 0.02180 0.01362 -0.0249 0.3409 1.0000
7.000 1.0513 0.02210 0.01398 -0.0234 0.3235 1.0000
7.250 1.0675 0.02244 0.01431 -0.0218 0.3051 1.0000
7.500 1.0825 0.02291 0.01470 -0.0201 0.2867 1.0000
7.750 1.0975 0.02360 0.01529 -0.0184 0.2696 1.0000
8.000 1.1113 0.02443 0.01613 -0.0167 0.2521 1.0000
8.250 1.1228 0.02537 0.01708 -0.0148 0.2328 1.0000
8.500 1.1308 0.02642 0.01812 -0.0124 0.2110 1.0000
8.750 1.1328 0.02754 0.01931 -0.0094 0.1844 1.0000
9.000 1.1288 0.02872 0.02052 -0.0057 0.1523 1.0000
9.250 1.1221 0.03025 0.02187 -0.0020 0.1253 1.0000
9.500 1.1167 0.03226 0.02364 0.0009 0.1093 1.0000
9.750 1.1154 0.03437 0.02562 0.0031 0.0981 1.0000
10.000 1.1182 0.03645 0.02765 0.0050 0.0898 1.0000
10.250 1.1252 0.03857 0.02958 0.0067 0.0834 1.0000
10.500 1.1366 0.04040 0.03154 0.0080 0.0784 1.0000
10.750 1.1634 0.04254 0.03338 0.0085 0.0723 1.0000
11.000 1.1695 0.04442 0.03557 0.0098 0.0696 1.0000
11.250 1.1811 0.04647 0.03780 0.0108 0.0667 1.0000
11.500 1.1981 0.04861 0.04001 0.0114 0.0641 1.0000
11.750 1.2303 0.05186 0.04320 0.0109 0.0611 1.0000
12.000 1.2244 0.05425 0.04591 0.0127 0.0602 1.0000
12.250 1.2182 0.05702 0.04898 0.0141 0.0592 1.0000
12.500 1.2110 0.06011 0.05236 0.0151 0.0582 1.0000
12.750 1.2018 0.06357 0.05610 0.0158 0.0575 1.0000
13.000 1.1897 0.06750 0.06029 0.0161 0.0572 1.0000
13.250 1.1738 0.07195 0.06502 0.0159 0.0570 1.0000
13.500 1.1536 0.07706 0.07039 0.0150 0.0571 1.0000
13.750 1.1292 0.08297 0.07657 0.0133 0.0573 1.0000
14.000 1.1009 0.08983 0.08366 0.0107 0.0577 1.0000
14.250 1.0688 0.09782 0.09189 0.0070 0.0584 1.0000
14.500 1.0336 0.10727 0.10153 0.0022 0.0592 1.0000
14.750 0.9968 0.11818 0.11260 -0.0037 0.0601 1.0000
15.000 0.9651 0.12935 0.12386 -0.0093 0.0611 1.0000
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