CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 50,000 Max Cl/Cd: 29.06 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkyh-il-50000.txt Download as CSV file: xf-clarkyh-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4921 0.12749 0.12041 0.0007 1.0000 0.2509
-11.250 -0.4537 0.12031 0.11314 0.0028 1.0000 0.2608
-11.000 -0.4846 0.12041 0.11340 -0.0006 1.0000 0.2674
-10.750 -0.4456 0.11337 0.10627 0.0013 1.0000 0.2751
-10.500 -0.4706 0.11264 0.10567 -0.0015 1.0000 0.2838
-10.250 -0.4375 0.10682 0.09978 0.0002 1.0000 0.2946
-10.000 -0.4432 0.10385 0.09688 -0.0010 1.0000 0.3035
-9.750 -0.4440 0.10130 0.09437 -0.0015 1.0000 0.3160
-9.500 -0.4263 0.09678 0.08985 -0.0011 1.0000 0.3237
-9.250 -0.4352 0.09419 0.08735 -0.0020 1.0000 0.3360
-9.000 -0.4511 0.09249 0.08577 -0.0026 1.0000 0.3507
-8.750 -0.4404 0.08896 0.08228 -0.0015 1.0000 0.3679
-8.500 -0.4213 0.08510 0.07842 -0.0002 1.0000 0.3860
-8.250 -0.4112 0.08188 0.07523 0.0008 1.0000 0.4036
-8.000 -0.3945 0.07864 0.07198 0.0021 1.0000 0.4240
-7.750 -0.5308 0.06135 0.05434 -0.0249 1.0000 0.2037
-7.500 -0.5266 0.05803 0.05097 -0.0230 1.0000 0.1987
-7.250 -0.5426 0.05272 0.04506 -0.0216 1.0000 0.1864
-7.000 -0.5370 0.04969 0.04190 -0.0196 1.0000 0.1848
-6.750 -0.5326 0.04675 0.03868 -0.0175 1.0000 0.1847
-6.500 -0.5264 0.04398 0.03550 -0.0156 1.0000 0.1857
-6.250 -0.5172 0.04135 0.03244 -0.0138 1.0000 0.1865
-6.000 -0.5049 0.03891 0.02960 -0.0122 1.0000 0.1873
-5.750 -0.4894 0.03716 0.02784 -0.0108 1.0000 0.1904
-5.500 -0.4738 0.03577 0.02628 -0.0094 1.0000 0.1958
-5.250 -0.4569 0.03416 0.02421 -0.0082 1.0000 0.2011
-5.000 -0.4385 0.03269 0.02256 -0.0073 1.0000 0.2060
-4.750 -0.4187 0.03154 0.02124 -0.0065 1.0000 0.2127
-4.500 -0.3984 0.03048 0.01998 -0.0059 1.0000 0.2229
-4.250 -0.3781 0.02960 0.01895 -0.0052 1.0000 0.2369
-4.000 -0.3572 0.02866 0.01797 -0.0047 1.0000 0.2543
-3.750 -0.3352 0.02771 0.01702 -0.0043 1.0000 0.2826
-3.500 -0.3127 0.02682 0.01638 -0.0040 1.0000 0.3285
-3.250 -0.2683 0.02598 0.01588 -0.0075 0.9923 0.4109
-3.000 -0.2204 0.02540 0.01579 -0.0118 0.9803 0.5025
-2.750 -0.0860 0.02432 0.01639 -0.0293 0.9765 1.0000
-2.500 -0.0308 0.02498 0.01647 -0.0357 0.9615 1.0000
-2.250 0.0192 0.02560 0.01672 -0.0409 0.9467 1.0000
-2.000 0.0650 0.02621 0.01706 -0.0453 0.9323 1.0000
-1.750 0.1088 0.02682 0.01744 -0.0491 0.9183 1.0000
-1.500 0.1539 0.02740 0.01783 -0.0531 0.9050 1.0000
-1.250 0.2028 0.02793 0.01820 -0.0576 0.8929 1.0000
-1.000 0.2286 0.02861 0.01878 -0.0582 0.8792 1.0000
-0.750 0.2512 0.02937 0.01944 -0.0581 0.8665 1.0000
-0.500 0.2806 0.03009 0.02007 -0.0592 0.8553 1.0000
-0.250 0.3155 0.03070 0.02061 -0.0610 0.8451 1.0000
0.000 0.3231 0.03171 0.02155 -0.0586 0.8333 1.0000
0.250 0.3460 0.03254 0.02233 -0.0585 0.8235 1.0000
0.500 0.3785 0.03311 0.02286 -0.0595 0.8127 1.0000
0.750 0.3883 0.03405 0.02376 -0.0572 0.8001 1.0000
1.000 0.4085 0.03479 0.02447 -0.0563 0.7880 1.0000
1.250 0.4409 0.03516 0.02483 -0.0567 0.7752 1.0000
1.500 0.4840 0.03506 0.02475 -0.0581 0.7624 1.0000
1.750 0.4980 0.03575 0.02544 -0.0560 0.7482 1.0000
2.000 0.5182 0.03619 0.02589 -0.0545 0.7337 1.0000
2.250 0.5373 0.03675 0.02647 -0.0529 0.7202 1.0000
2.500 0.5590 0.03731 0.02707 -0.0518 0.7083 1.0000
2.750 0.5940 0.03718 0.02700 -0.0517 0.6969 1.0000
3.000 0.6204 0.03731 0.02720 -0.0506 0.6838 1.0000
3.250 0.6394 0.03781 0.02777 -0.0488 0.6692 1.0000
3.500 0.6610 0.03815 0.02819 -0.0472 0.6543 1.0000
3.750 0.6858 0.03825 0.02836 -0.0456 0.6387 1.0000
4.000 0.7136 0.03804 0.02826 -0.0440 0.6221 1.0000
4.250 0.7439 0.03760 0.02791 -0.0424 0.6047 1.0000
4.500 0.7752 0.03707 0.02746 -0.0408 0.5869 1.0000
4.750 0.8059 0.03670 0.02716 -0.0393 0.5689 1.0000
5.000 0.8148 0.03809 0.02864 -0.0368 0.5466 1.0000
5.250 0.8341 0.03877 0.02938 -0.0350 0.5278 1.0000
5.500 0.8540 0.03948 0.03016 -0.0333 0.5111 1.0000
5.750 0.8709 0.04063 0.03141 -0.0318 0.4964 1.0000
6.000 0.8916 0.04157 0.03244 -0.0306 0.4841 1.0000
6.250 0.9295 0.04077 0.03167 -0.0299 0.4721 1.0000
6.500 0.9403 0.04222 0.03328 -0.0281 0.4578 1.0000
6.750 0.9500 0.04371 0.03489 -0.0262 0.4436 1.0000
7.000 0.9714 0.04387 0.03515 -0.0245 0.4283 1.0000
7.250 0.9970 0.04356 0.03492 -0.0229 0.4124 1.0000
7.500 1.0120 0.04446 0.03598 -0.0212 0.3981 1.0000
7.750 1.0303 0.04506 0.03672 -0.0195 0.3834 1.0000
8.000 1.0847 0.04172 0.03328 -0.0189 0.3599 1.0000
8.250 1.0908 0.04214 0.03387 -0.0159 0.3368 1.0000
8.500 1.1244 0.03869 0.03002 -0.0135 0.2987 1.0000
8.750 1.1333 0.03901 0.03013 -0.0104 0.2655 1.0000
9.000 1.1415 0.04066 0.03145 -0.0076 0.2295 1.0000
9.250 1.1461 0.04317 0.03377 -0.0049 0.1994 1.0000
9.500 1.1564 0.04534 0.03569 -0.0030 0.1754 1.0000
9.750 1.1591 0.04749 0.03791 -0.0005 0.1604 1.0000
10.000 1.1598 0.04976 0.04038 0.0020 0.1496 1.0000
10.250 1.1571 0.05248 0.04333 0.0045 0.1418 1.0000
10.500 1.1703 0.05433 0.04506 0.0057 0.1330 1.0000
10.750 1.1559 0.05783 0.04894 0.0086 0.1300 1.0000
11.000 1.1443 0.06140 0.05278 0.0107 0.1271 1.0000
11.250 1.1644 0.06341 0.05464 0.0112 0.1206 1.0000
11.500 1.1407 0.06784 0.05940 0.0128 0.1200 1.0000
11.750 1.1142 0.07298 0.06481 0.0134 0.1198 1.0000
12.000 1.0849 0.07898 0.07104 0.0128 0.1202 1.0000
12.250 1.0544 0.08591 0.07814 0.0111 0.1208 1.0000
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Polar data table (+)
Polar graphs
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