CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 100,000 Max Cl/Cd: 49.18 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkyh-il-100000-n5.txt Download as CSV file: xf-clarkyh-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5726 0.09821 0.09325 -0.0178 1.0000 0.0437
-12.000 -0.6689 0.06830 0.06339 -0.0429 1.0000 0.0425
-11.750 -0.7042 0.05953 0.05443 -0.0498 1.0000 0.0421
-11.500 -0.7375 0.05338 0.04796 -0.0505 1.0000 0.0422
-11.250 -0.7567 0.04829 0.04244 -0.0496 1.0000 0.0430
-11.000 -0.7414 0.04732 0.04154 -0.0487 1.0000 0.0444
-10.750 -0.7343 0.04522 0.03930 -0.0475 1.0000 0.0459
-10.500 -0.7322 0.04222 0.03597 -0.0460 1.0000 0.0478
-10.250 -0.7322 0.03887 0.03207 -0.0439 1.0000 0.0501
-10.000 -0.7290 0.03607 0.02873 -0.0414 1.0000 0.0523
-9.750 -0.7151 0.03484 0.02753 -0.0397 1.0000 0.0542
-9.500 -0.7048 0.03366 0.02623 -0.0373 1.0000 0.0564
-9.250 -0.6973 0.03223 0.02450 -0.0343 1.0000 0.0589
-9.000 -0.6908 0.03071 0.02251 -0.0311 1.0000 0.0612
-8.750 -0.6688 0.02951 0.02135 -0.0307 0.9964 0.0637
-8.500 -0.6374 0.02839 0.02007 -0.0319 0.9895 0.0669
-8.250 -0.6048 0.02703 0.01832 -0.0332 0.9835 0.0706
-8.000 -0.5728 0.02589 0.01710 -0.0344 0.9766 0.0733
-7.750 -0.5381 0.02506 0.01617 -0.0360 0.9710 0.0766
-7.500 -0.5059 0.02415 0.01504 -0.0369 0.9635 0.0799
-7.250 -0.4712 0.02316 0.01384 -0.0382 0.9569 0.0824
-7.000 -0.4391 0.02239 0.01307 -0.0391 0.9479 0.0853
-6.750 -0.4065 0.02171 0.01228 -0.0399 0.9384 0.0891
-6.500 -0.3729 0.02100 0.01140 -0.0407 0.9285 0.0925
-6.250 -0.3449 0.02032 0.01065 -0.0405 0.9157 0.0953
-6.000 -0.3180 0.01970 0.01001 -0.0400 0.9038 0.0990
-5.750 -0.2906 0.01917 0.00937 -0.0396 0.8939 0.1039
-5.500 -0.2661 0.01862 0.00882 -0.0387 0.8829 0.1106
-5.250 -0.2415 0.01811 0.00827 -0.0378 0.8724 0.1201
-5.000 -0.2166 0.01756 0.00784 -0.0370 0.8631 0.1335
-4.750 -0.1925 0.01722 0.00771 -0.0361 0.8514 0.1564
-4.500 -0.1665 0.01708 0.00751 -0.0353 0.8405 0.1904
-4.250 -0.1405 0.01690 0.00726 -0.0345 0.8305 0.2122
-4.000 -0.1154 0.01672 0.00705 -0.0337 0.8183 0.2303
-3.750 -0.0901 0.01652 0.00683 -0.0329 0.8066 0.2469
-3.500 -0.0645 0.01631 0.00661 -0.0322 0.7958 0.2622
-3.250 -0.0390 0.01609 0.00641 -0.0314 0.7841 0.2792
-3.000 -0.0136 0.01588 0.00625 -0.0308 0.7715 0.2987
-2.750 0.0121 0.01566 0.00607 -0.0301 0.7593 0.3182
-2.500 0.0379 0.01544 0.00589 -0.0295 0.7474 0.3396
-2.250 0.0633 0.01513 0.00573 -0.0288 0.7350 0.3796
-2.000 0.0868 0.01460 0.00558 -0.0279 0.7220 0.4696
-1.750 0.1419 0.01364 0.00596 -0.0316 0.7100 0.8682
-1.500 0.1881 0.01376 0.00597 -0.0345 0.6968 0.9187
-1.250 0.2264 0.01389 0.00595 -0.0360 0.6834 0.9473
-1.000 0.2682 0.01402 0.00589 -0.0384 0.6690 0.9720
-0.750 0.3208 0.01407 0.00575 -0.0433 0.6535 0.9927
-0.500 0.3595 0.01408 0.00561 -0.0456 0.6397 1.0000
-0.250 0.3842 0.01416 0.00559 -0.0450 0.6275 1.0000
0.000 0.4088 0.01426 0.00558 -0.0445 0.6164 1.0000
0.250 0.4333 0.01436 0.00556 -0.0439 0.6061 1.0000
0.500 0.4579 0.01448 0.00564 -0.0434 0.5949 1.0000
0.750 0.4824 0.01461 0.00570 -0.0429 0.5852 1.0000
1.000 0.5068 0.01474 0.00578 -0.0423 0.5756 1.0000
1.250 0.5312 0.01488 0.00590 -0.0418 0.5654 1.0000
1.500 0.5554 0.01502 0.00598 -0.0412 0.5560 1.0000
1.750 0.5796 0.01517 0.00614 -0.0407 0.5459 1.0000
2.000 0.6038 0.01533 0.00629 -0.0401 0.5377 1.0000
2.250 0.6277 0.01549 0.00645 -0.0396 0.5279 1.0000
2.500 0.6515 0.01565 0.00663 -0.0390 0.5180 1.0000
2.750 0.6750 0.01581 0.00676 -0.0383 0.5076 1.0000
3.000 0.6984 0.01598 0.00695 -0.0376 0.4958 1.0000
3.250 0.7217 0.01617 0.00718 -0.0369 0.4849 1.0000
3.500 0.7449 0.01637 0.00737 -0.0362 0.4750 1.0000
3.750 0.7680 0.01658 0.00762 -0.0355 0.4639 1.0000
4.000 0.7907 0.01681 0.00789 -0.0347 0.4516 1.0000
4.250 0.8129 0.01706 0.00815 -0.0338 0.4381 1.0000
4.500 0.8348 0.01734 0.00844 -0.0329 0.4232 1.0000
4.750 0.8562 0.01763 0.00876 -0.0320 0.4067 1.0000
5.000 0.8771 0.01795 0.00912 -0.0310 0.3884 1.0000
5.250 0.8976 0.01829 0.00949 -0.0300 0.3678 1.0000
5.500 0.9177 0.01866 0.00988 -0.0289 0.3457 1.0000
5.750 0.9372 0.01906 0.01029 -0.0277 0.3219 1.0000
6.000 0.9556 0.01954 0.01071 -0.0265 0.3021 1.0000
6.250 0.9736 0.02008 0.01120 -0.0251 0.2869 1.0000
6.500 0.9912 0.02066 0.01175 -0.0238 0.2745 1.0000
6.750 1.0085 0.02128 0.01236 -0.0225 0.2633 1.0000
7.000 1.0249 0.02198 0.01303 -0.0211 0.2521 1.0000
7.250 1.0396 0.02276 0.01377 -0.0195 0.2395 1.0000
7.500 1.0533 0.02359 0.01456 -0.0179 0.2255 1.0000
7.750 1.0673 0.02436 0.01538 -0.0163 0.2112 1.0000
8.000 1.0811 0.02510 0.01621 -0.0148 0.1972 1.0000
8.250 1.0945 0.02583 0.01704 -0.0132 0.1826 1.0000
8.500 1.1071 0.02656 0.01790 -0.0116 0.1649 1.0000
8.750 1.1182 0.02736 0.01878 -0.0099 0.1391 1.0000
9.000 1.1184 0.02869 0.01987 -0.0071 0.1042 1.0000
9.250 1.1141 0.03057 0.02150 -0.0043 0.0861 1.0000
9.500 1.1129 0.03250 0.02340 -0.0021 0.0738 1.0000
9.750 1.1130 0.03451 0.02545 -0.0004 0.0634 1.0000
10.000 1.1133 0.03661 0.02760 0.0010 0.0553 1.0000
10.250 1.1139 0.03880 0.02984 0.0021 0.0494 1.0000
10.500 1.1140 0.04113 0.03228 0.0030 0.0456 1.0000
10.750 1.1135 0.04364 0.03488 0.0035 0.0427 1.0000
11.000 1.1106 0.04651 0.03781 0.0038 0.0404 1.0000
11.250 1.1060 0.04969 0.04104 0.0039 0.0387 1.0000
11.500 1.1040 0.05271 0.04423 0.0038 0.0371 1.0000
11.750 1.1010 0.05593 0.04758 0.0036 0.0357 1.0000
12.000 1.0974 0.05928 0.05106 0.0032 0.0345 1.0000
12.250 1.0934 0.06275 0.05464 0.0028 0.0335 1.0000
12.500 1.0893 0.06629 0.05828 0.0022 0.0326 1.0000
12.750 1.0849 0.06991 0.06199 0.0016 0.0317 1.0000
13.000 1.0811 0.07345 0.06557 0.0011 0.0308 1.0000
13.250 1.0804 0.07657 0.06875 0.0010 0.0298 1.0000
13.500 1.0800 0.07990 0.07228 0.0004 0.0290 1.0000
13.750 1.0793 0.08334 0.07587 -0.0003 0.0282 1.0000
14.000 1.0787 0.08681 0.07948 -0.0009 0.0275 1.0000
14.250 1.0776 0.09040 0.08321 -0.0016 0.0270 1.0000
14.500 1.0752 0.09428 0.08724 -0.0026 0.0265 1.0000
14.750 1.0718 0.09845 0.09155 -0.0039 0.0260 1.0000
15.000 1.0670 0.10296 0.09620 -0.0055 0.0255 1.0000
15.250 1.0613 0.10772 0.10110 -0.0073 0.0251 1.0000
15.500 1.0548 0.11272 0.10622 -0.0093 0.0247 1.0000
15.750 1.0477 0.11799 0.11162 -0.0116 0.0244 1.0000
16.000 1.0400 0.12351 0.11725 -0.0142 0.0240 1.0000
16.250 1.0310 0.12947 0.12334 -0.0170 0.0237 1.0000
16.500 1.0189 0.13642 0.13044 -0.0206 0.0236 1.0000
16.750 0.9999 0.14566 0.13989 -0.0257 0.0236 1.0000
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