CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 50,000 Max Cl/Cd: 33.01 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkyh-il-50000-n5.txt Download as CSV file: xf-clarkyh-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5239 0.09649 0.08945 -0.0233 1.0000 0.0795
-11.000 -0.5328 0.09029 0.08331 -0.0276 1.0000 0.0797
-10.750 -0.5465 0.08304 0.07614 -0.0337 1.0000 0.0800
-10.500 -0.5672 0.07540 0.06853 -0.0394 1.0000 0.0801
-10.250 -0.5909 0.06847 0.06151 -0.0425 1.0000 0.0803
-10.000 -0.6129 0.06201 0.05481 -0.0440 1.0000 0.0808
-9.750 -0.6312 0.05611 0.04849 -0.0439 1.0000 0.0818
-9.500 -0.6213 0.05395 0.04634 -0.0426 1.0000 0.0839
-9.250 -0.6141 0.05169 0.04397 -0.0412 1.0000 0.0863
-9.000 -0.6135 0.04868 0.04067 -0.0393 1.0000 0.0891
-8.750 -0.6158 0.04537 0.03693 -0.0367 1.0000 0.0915
-8.500 -0.6171 0.04226 0.03323 -0.0336 1.0000 0.0935
-8.250 -0.6077 0.04057 0.03146 -0.0313 1.0000 0.0961
-8.000 -0.5973 0.03922 0.03001 -0.0290 1.0000 0.0994
-7.750 -0.5880 0.03739 0.02787 -0.0265 1.0000 0.1024
-7.500 -0.5771 0.03542 0.02547 -0.0242 1.0000 0.1048
-7.250 -0.5641 0.03374 0.02340 -0.0222 1.0000 0.1080
-7.000 -0.5489 0.03267 0.02233 -0.0205 1.0000 0.1116
-6.750 -0.5328 0.03150 0.02098 -0.0188 1.0000 0.1153
-6.500 -0.5116 0.03018 0.01936 -0.0180 0.9985 0.1186
-6.250 -0.4734 0.02879 0.01772 -0.0202 0.9905 0.1230
-6.000 -0.4347 0.02786 0.01675 -0.0226 0.9821 0.1300
-5.750 -0.3942 0.02700 0.01583 -0.0253 0.9730 0.1391
-5.500 -0.3524 0.02622 0.01496 -0.0279 0.9625 0.1495
-5.250 -0.3092 0.02561 0.01434 -0.0308 0.9515 0.1639
-5.000 -0.2622 0.02501 0.01362 -0.0343 0.9416 0.1904
-4.750 -0.2204 0.02448 0.01304 -0.0369 0.9302 0.2243
-4.500 -0.1839 0.02397 0.01254 -0.0386 0.9180 0.2584
-4.250 -0.1484 0.02349 0.01214 -0.0401 0.9068 0.2933
-4.000 -0.1136 0.02305 0.01178 -0.0413 0.8959 0.3270
-3.750 -0.0849 0.02268 0.01150 -0.0414 0.8829 0.3593
-3.500 -0.0574 0.02226 0.01125 -0.0412 0.8703 0.4000
-3.250 -0.0309 0.02172 0.01100 -0.0407 0.8586 0.4533
-3.000 -0.0059 0.02086 0.01078 -0.0396 0.8478 0.5580
-2.750 0.0990 0.02042 0.01113 -0.0509 0.8436 0.9235
-2.500 0.1632 0.02049 0.01090 -0.0573 0.8338 0.9822
-2.250 0.2107 0.02041 0.01058 -0.0613 0.8212 1.0000
-2.000 0.2334 0.02050 0.01049 -0.0603 0.8071 1.0000
-1.750 0.2560 0.02059 0.01043 -0.0593 0.7939 1.0000
-1.500 0.2791 0.02067 0.01035 -0.0583 0.7819 1.0000
-1.250 0.3008 0.02082 0.01038 -0.0572 0.7683 1.0000
-1.000 0.3227 0.02098 0.01044 -0.0562 0.7553 1.0000
-0.750 0.3448 0.02114 0.01050 -0.0552 0.7432 1.0000
-0.500 0.3678 0.02124 0.01049 -0.0542 0.7330 1.0000
-0.250 0.3897 0.02144 0.01063 -0.0532 0.7213 1.0000
0.000 0.4121 0.02165 0.01078 -0.0523 0.7099 1.0000
0.250 0.4352 0.02176 0.01081 -0.0513 0.6995 1.0000
0.500 0.4580 0.02187 0.01084 -0.0502 0.6884 1.0000
0.750 0.4799 0.02205 0.01099 -0.0491 0.6761 1.0000
1.000 0.5025 0.02218 0.01106 -0.0479 0.6646 1.0000
1.250 0.5263 0.02222 0.01102 -0.0467 0.6545 1.0000
1.500 0.5480 0.02248 0.01127 -0.0457 0.6424 1.0000
1.750 0.5702 0.02272 0.01149 -0.0446 0.6312 1.0000
2.000 0.5940 0.02284 0.01156 -0.0436 0.6214 1.0000
2.250 0.6155 0.02317 0.01191 -0.0425 0.6097 1.0000
2.500 0.6372 0.02347 0.01223 -0.0414 0.5981 1.0000
2.750 0.6600 0.02365 0.01241 -0.0403 0.5868 1.0000
3.000 0.6819 0.02389 0.01266 -0.0392 0.5744 1.0000
3.250 0.7022 0.02427 0.01311 -0.0380 0.5619 1.0000
3.500 0.7236 0.02460 0.01352 -0.0369 0.5506 1.0000
3.750 0.7465 0.02481 0.01375 -0.0359 0.5400 1.0000
4.000 0.7663 0.02522 0.01427 -0.0347 0.5274 1.0000
4.250 0.7864 0.02561 0.01477 -0.0335 0.5146 1.0000
4.500 0.8069 0.02593 0.01517 -0.0323 0.5014 1.0000
4.750 0.8276 0.02622 0.01553 -0.0310 0.4875 1.0000
5.000 0.8482 0.02650 0.01590 -0.0297 0.4730 1.0000
5.250 0.8687 0.02682 0.01628 -0.0284 0.4579 1.0000
5.500 0.8892 0.02720 0.01671 -0.0272 0.4428 1.0000
5.750 0.9095 0.02763 0.01722 -0.0259 0.4274 1.0000
6.000 0.9290 0.02814 0.01779 -0.0247 0.4113 1.0000
6.250 0.9473 0.02872 0.01844 -0.0233 0.3948 1.0000
6.500 0.9644 0.02936 0.01918 -0.0219 0.3782 1.0000
6.750 0.9809 0.03001 0.01993 -0.0204 0.3622 1.0000
7.000 0.9968 0.03067 0.02069 -0.0189 0.3469 1.0000
7.250 1.0120 0.03136 0.02148 -0.0174 0.3322 1.0000
7.500 1.0267 0.03213 0.02237 -0.0159 0.3185 1.0000
7.750 1.0407 0.03291 0.02327 -0.0143 0.3053 1.0000
8.000 1.0537 0.03369 0.02412 -0.0126 0.2917 1.0000
8.250 1.0659 0.03454 0.02501 -0.0109 0.2784 1.0000
8.500 1.0752 0.03548 0.02595 -0.0089 0.2633 1.0000
8.750 1.0796 0.03660 0.02700 -0.0066 0.2457 1.0000
9.000 1.0787 0.03796 0.02830 -0.0038 0.2278 1.0000
9.250 1.0750 0.03962 0.02993 -0.0013 0.2108 1.0000
9.500 1.0714 0.04155 0.03196 0.0006 0.1949 1.0000
9.750 1.0675 0.04375 0.03431 0.0020 0.1790 1.0000
10.000 1.0629 0.04622 0.03694 0.0030 0.1619 1.0000
10.250 1.0578 0.04903 0.03991 0.0035 0.1422 1.0000
10.500 1.0517 0.05213 0.04302 0.0037 0.1237 1.0000
10.750 1.0443 0.05555 0.04632 0.0036 0.1095 1.0000
11.000 1.0365 0.05922 0.04986 0.0034 0.0988 1.0000
11.250 1.0292 0.06299 0.05352 0.0033 0.0907 1.0000
11.500 1.0222 0.06677 0.05722 0.0031 0.0844 1.0000
11.750 1.0179 0.07038 0.06086 0.0030 0.0786 1.0000
12.000 1.0144 0.07399 0.06457 0.0028 0.0734 1.0000
12.250 1.0116 0.07737 0.06789 0.0027 0.0695 1.0000
12.500 1.0099 0.08110 0.07183 0.0024 0.0659 1.0000
12.750 1.0078 0.08490 0.07583 0.0019 0.0628 1.0000
13.000 1.0061 0.08857 0.07957 0.0013 0.0600 1.0000
13.250 1.0070 0.09176 0.08273 0.0010 0.0576 1.0000
13.500 0.9996 0.09691 0.08818 -0.0006 0.0559 1.0000
13.750 0.9909 0.10242 0.09395 -0.0025 0.0546 1.0000
14.000 0.9803 0.10847 0.10022 -0.0047 0.0535 1.0000
14.250 0.9666 0.11539 0.10736 -0.0077 0.0529 1.0000
14.500 0.9475 0.12395 0.11612 -0.0116 0.0526 1.0000
14.750 0.9188 0.13571 0.12808 -0.0174 0.0530 1.0000
15.000 0.8839 0.15076 0.14319 -0.0248 0.0536 1.0000
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Polar data table (+)
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