CLARK YM-18 AIRFOIL (clarym18-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YM-18 AIRFOIL (clarym18-il) Reynolds number: 50,000 Max Cl/Cd: 7.57 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarym18-il-50000.txt Download as CSV file: xf-clarym18-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YM-18 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3032 0.12202 0.11506 -0.0200 1.0000 0.3229
-9.000 -0.3044 0.12039 0.11349 -0.0177 1.0000 0.3312
-8.750 -0.3569 0.12194 0.11522 -0.0144 1.0000 0.3376
-8.500 -0.3261 0.11710 0.11037 -0.0131 1.0000 0.3438
-8.250 -0.3320 0.11568 0.10901 -0.0107 1.0000 0.3526
-8.000 -0.3975 0.11737 0.11091 -0.0067 1.0000 0.3584
-7.750 -0.3530 0.11198 0.10547 -0.0061 1.0000 0.3647
-7.500 -0.6042 0.08742 0.08095 -0.0219 1.0000 0.2039
-7.250 -0.6118 0.08376 0.07730 -0.0204 1.0000 0.2022
-7.000 -0.6281 0.07907 0.07255 -0.0196 1.0000 0.1997
-6.750 -0.6495 0.07304 0.06634 -0.0194 1.0000 0.1965
-6.500 -0.6673 0.06647 0.05941 -0.0197 1.0000 0.1942
-6.250 -0.6714 0.06162 0.05422 -0.0194 1.0000 0.1945
-6.000 -0.6678 0.05798 0.05026 -0.0188 1.0000 0.1968
-5.750 -0.6615 0.05441 0.04625 -0.0184 1.0000 0.2005
-5.500 -0.6528 0.05062 0.04172 -0.0184 1.0000 0.2048
-5.250 -0.6370 0.04989 0.04126 -0.0171 1.0000 0.2103
-5.000 -0.6222 0.04822 0.03933 -0.0165 1.0000 0.2173
-4.750 -0.6064 0.04622 0.03695 -0.0162 1.0000 0.2245
-4.500 -0.5898 0.04555 0.03633 -0.0153 1.0000 0.2326
-4.250 -0.5719 0.04405 0.03445 -0.0151 1.0000 0.2420
-4.000 -0.5545 0.04350 0.03397 -0.0143 1.0000 0.2515
-3.750 -0.5358 0.04252 0.03276 -0.0140 1.0000 0.2625
-3.500 -0.5172 0.04195 0.03209 -0.0135 1.0000 0.2749
-3.250 -0.4987 0.04137 0.03155 -0.0130 1.0000 0.2875
-3.000 -0.4793 0.04081 0.03089 -0.0127 1.0000 0.3028
-2.750 -0.4598 0.04038 0.03040 -0.0124 1.0000 0.3209
-2.500 -0.3827 0.04129 0.03145 -0.0219 0.9765 0.3658
-2.250 -0.3372 0.04148 0.03179 -0.0256 0.9615 0.4082
-2.000 -0.2947 0.04171 0.03219 -0.0286 0.9459 0.4559
-1.750 -0.2540 0.04197 0.03266 -0.0310 0.9291 0.5056
-1.500 -0.2149 0.04224 0.03318 -0.0328 0.9122 0.5593
-1.250 -0.1775 0.04249 0.03375 -0.0338 0.8963 0.6206
-1.000 -0.1415 0.04275 0.03445 -0.0337 0.8818 0.6974
-0.750 -0.1296 0.04275 0.03488 -0.0293 0.8677 0.7787
-0.500 0.0037 0.04496 0.03718 -0.0445 0.8485 0.9709
-0.250 0.0771 0.04528 0.03707 -0.0561 0.8315 1.0000
0.000 0.0870 0.04537 0.03689 -0.0548 0.8172 1.0000
0.250 0.1216 0.04567 0.03692 -0.0566 0.8038 1.0000
0.500 0.1449 0.04600 0.03704 -0.0564 0.7887 1.0000
0.750 0.1582 0.04652 0.03740 -0.0549 0.7725 1.0000
1.000 0.1780 0.04710 0.03782 -0.0542 0.7568 1.0000
1.250 0.2057 0.04760 0.03816 -0.0544 0.7419 1.0000
1.500 0.2544 0.04767 0.03806 -0.0570 0.7300 1.0000
2.000 0.2769 0.04948 0.03966 -0.0535 0.6977 1.0000
2.250 0.2979 0.05027 0.04034 -0.0529 0.6837 1.0000
2.500 0.3428 0.05019 0.04014 -0.0545 0.6735 1.0000
2.750 0.3420 0.05191 0.04179 -0.0519 0.6583 1.0000
3.000 0.3540 0.05333 0.04313 -0.0508 0.6464 1.0000
3.250 0.3872 0.05375 0.04345 -0.0513 0.6369 1.0000
3.500 0.3816 0.05613 0.04578 -0.0489 0.6242 1.0000
3.750 0.4244 0.05610 0.04566 -0.0500 0.6170 1.0000
4.000 0.4025 0.05977 0.04931 -0.0472 0.6061 1.0000
4.250 0.4344 0.06047 0.04994 -0.0477 0.5991 1.0000
4.500 0.4238 0.06369 0.05314 -0.0459 0.5906 1.0000
4.750 0.4335 0.06575 0.05516 -0.0453 0.5834 1.0000
5.250 0.4430 0.07100 0.06036 -0.0442 0.5731 1.0000
5.500 0.4388 0.07414 0.06349 -0.0434 0.5686 1.0000
5.750 0.4513 0.07639 0.06572 -0.0434 0.5641 1.0000
6.000 0.4863 0.07756 0.06685 -0.0441 0.5588 1.0000
6.250 0.4740 0.08153 0.07084 -0.0434 0.5576 1.0000
6.500 0.4698 0.08507 0.07439 -0.0432 0.5572 1.0000
6.750 0.4749 0.08840 0.07772 -0.0435 0.5581 1.0000
7.000 0.4874 0.09165 0.08099 -0.0443 0.5593 1.0000
7.250 0.3838 0.10247 0.09203 -0.0457 0.6555 1.0000
7.500 0.3909 0.10500 0.09455 -0.0455 0.6509 1.0000
7.750 0.3977 0.10647 0.09602 -0.0448 0.6394 1.0000
8.000 0.4317 0.11080 0.10035 -0.0471 0.6339 1.0000
8.250 0.4172 0.11102 0.10058 -0.0446 0.6232 1.0000
8.500 0.4589 0.11567 0.10524 -0.0473 0.6159 1.0000
8.750 0.4399 0.11579 0.10537 -0.0447 0.6056 1.0000
9.000 0.4745 0.11985 0.10944 -0.0467 0.5979 1.0000
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Polar data table (+)
Polar graphs
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