CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 500,000 Max Cl/Cd: 84.05 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkyh-il-500000.txt Download as CSV file: xf-clarkyh-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -1.0742 0.04505 0.04180 -0.0586 1.0000 0.0212
-15.000 -1.0853 0.04120 0.03777 -0.0599 1.0000 0.0214
-14.750 -1.0910 0.03852 0.03493 -0.0592 1.0000 0.0217
-14.500 -1.0940 0.03633 0.03258 -0.0575 1.0000 0.0221
-14.250 -1.0944 0.03443 0.03049 -0.0553 1.0000 0.0225
-14.000 -1.0908 0.03267 0.02852 -0.0531 1.0000 0.0231
-13.750 -1.0814 0.03115 0.02676 -0.0514 1.0000 0.0235
-13.500 -1.0741 0.02923 0.02472 -0.0495 1.0000 0.0243
-13.250 -1.0544 0.02874 0.02423 -0.0484 1.0000 0.0249
-13.000 -1.0339 0.02829 0.02376 -0.0474 1.0000 0.0255
-12.750 -1.0150 0.02753 0.02290 -0.0462 1.0000 0.0263
-12.500 -0.9974 0.02648 0.02167 -0.0449 1.0000 0.0272
-12.250 -0.9788 0.02549 0.02047 -0.0436 1.0000 0.0280
-12.000 -0.9614 0.02425 0.01916 -0.0424 1.0000 0.0290
-11.750 -0.9374 0.02412 0.01906 -0.0416 1.0000 0.0298
-11.500 -0.9136 0.02394 0.01885 -0.0409 1.0000 0.0307
-11.250 -0.8916 0.02344 0.01825 -0.0399 1.0000 0.0320
-11.000 -0.8708 0.02289 0.01752 -0.0388 1.0000 0.0331
-10.750 -0.8516 0.02169 0.01622 -0.0377 0.9972 0.0342
-10.500 -0.8180 0.02132 0.01588 -0.0390 0.9896 0.0354
-10.250 -0.7840 0.02103 0.01552 -0.0403 0.9816 0.0369
-10.000 -0.7525 0.02063 0.01499 -0.0410 0.9719 0.0386
-9.750 -0.7243 0.02032 0.01449 -0.0408 0.9608 0.0398
-9.500 -0.7017 0.01889 0.01305 -0.0401 0.9506 0.0414
-9.250 -0.6784 0.01854 0.01266 -0.0390 0.9410 0.0428
-9.000 -0.6549 0.01819 0.01223 -0.0380 0.9319 0.0444
-8.750 -0.6318 0.01787 0.01178 -0.0367 0.9237 0.0459
-8.500 -0.6072 0.01772 0.01151 -0.0357 0.9150 0.0470
-8.250 -0.5862 0.01626 0.00996 -0.0344 0.9077 0.0489
-8.000 -0.5620 0.01567 0.00936 -0.0335 0.8995 0.0505
-7.750 -0.5382 0.01524 0.00885 -0.0324 0.8922 0.0521
-7.500 -0.5128 0.01481 0.00837 -0.0317 0.8842 0.0537
-7.250 -0.4878 0.01447 0.00793 -0.0308 0.8774 0.0550
-7.000 -0.4615 0.01417 0.00756 -0.0302 0.8705 0.0559
-6.750 -0.4381 0.01325 0.00658 -0.0291 0.8636 0.0578
-6.500 -0.4133 0.01274 0.00603 -0.0283 0.8568 0.0595
-6.250 -0.3878 0.01235 0.00561 -0.0276 0.8490 0.0610
-6.000 -0.3622 0.01203 0.00524 -0.0268 0.8418 0.0626
-5.750 -0.3361 0.01171 0.00488 -0.0262 0.8335 0.0640
-5.500 -0.3100 0.01144 0.00453 -0.0255 0.8260 0.0652
-5.250 -0.2836 0.01115 0.00421 -0.0250 0.8172 0.0664
-5.000 -0.2577 0.01083 0.00385 -0.0243 0.8089 0.0692
-4.750 -0.2311 0.01058 0.00360 -0.0237 0.7991 0.0719
-4.500 -0.2043 0.01037 0.00337 -0.0233 0.7892 0.0748
-4.250 -0.1777 0.01017 0.00315 -0.0227 0.7787 0.0797
-4.000 -0.1507 0.00998 0.00297 -0.0223 0.7646 0.0891
-3.750 -0.1243 0.00975 0.00275 -0.0217 0.7489 0.1048
-3.500 -0.0984 0.00946 0.00250 -0.0211 0.7318 0.1267
-3.250 -0.0724 0.00924 0.00245 -0.0207 0.7138 0.1871
-3.000 -0.0450 0.00923 0.00238 -0.0204 0.6952 0.2028
-2.750 -0.0181 0.00919 0.00229 -0.0200 0.6767 0.2146
-2.500 0.0089 0.00920 0.00222 -0.0196 0.6591 0.2224
-2.250 0.0359 0.00920 0.00216 -0.0193 0.6443 0.2311
-2.000 0.0630 0.00921 0.00211 -0.0191 0.6317 0.2392
-1.750 0.0901 0.00920 0.00208 -0.0188 0.6202 0.2471
-1.500 0.1175 0.00919 0.00204 -0.0186 0.6092 0.2538
-1.250 0.1445 0.00917 0.00202 -0.0184 0.5988 0.2621
-1.000 0.1716 0.00914 0.00199 -0.0182 0.5875 0.2718
-0.750 0.1985 0.00907 0.00197 -0.0180 0.5758 0.2894
-0.500 0.2243 0.00893 0.00196 -0.0176 0.5639 0.3334
-0.250 0.2460 0.00842 0.00194 -0.0166 0.5529 0.4891
0.000 0.2554 0.00726 0.00197 -0.0125 0.5434 0.8358
0.250 0.2942 0.00724 0.00213 -0.0144 0.5315 0.9124
0.500 0.3468 0.00748 0.00235 -0.0195 0.5183 0.9463
0.750 0.3853 0.00770 0.00252 -0.0216 0.5066 0.9633
1.000 0.4246 0.00791 0.00268 -0.0239 0.4952 0.9744
1.250 0.4628 0.00812 0.00282 -0.0261 0.4853 0.9831
1.500 0.5076 0.00827 0.00290 -0.0298 0.4741 0.9872
1.750 0.5462 0.00839 0.00298 -0.0322 0.4625 0.9915
2.000 0.5829 0.00852 0.00305 -0.0343 0.4500 0.9946
2.250 0.6228 0.00864 0.00311 -0.0372 0.4388 0.9976
2.500 0.6602 0.00873 0.00318 -0.0395 0.4281 1.0000
2.750 0.6856 0.00882 0.00325 -0.0392 0.4178 1.0000
3.000 0.7107 0.00895 0.00333 -0.0389 0.4069 1.0000
3.250 0.7358 0.00905 0.00342 -0.0386 0.3938 1.0000
3.500 0.7607 0.00918 0.00351 -0.0383 0.3775 1.0000
3.750 0.7850 0.00934 0.00361 -0.0379 0.3506 1.0000
4.000 0.8066 0.00986 0.00380 -0.0372 0.2829 1.0000
4.250 0.8280 0.01039 0.00414 -0.0365 0.2525 1.0000
4.500 0.8500 0.01079 0.00444 -0.0358 0.2390 1.0000
4.750 0.8727 0.01109 0.00471 -0.0351 0.2298 1.0000
5.000 0.8949 0.01141 0.00501 -0.0344 0.2217 1.0000
5.250 0.9179 0.01165 0.00526 -0.0338 0.2160 1.0000
5.500 0.9398 0.01197 0.00556 -0.0330 0.2103 1.0000
5.750 0.9625 0.01221 0.00583 -0.0324 0.2048 1.0000
6.000 0.9852 0.01244 0.00608 -0.0317 0.1983 1.0000
6.250 1.0062 0.01280 0.00642 -0.0309 0.1915 1.0000
6.500 1.0299 0.01294 0.00661 -0.0304 0.1850 1.0000
6.750 1.0511 0.01326 0.00691 -0.0295 0.1766 1.0000
7.000 1.0741 0.01344 0.00713 -0.0290 0.1663 1.0000
7.250 1.0951 0.01377 0.00740 -0.0282 0.1494 1.0000
7.500 1.1098 0.01456 0.00788 -0.0265 0.1005 1.0000
7.750 1.1224 0.01546 0.00864 -0.0245 0.0791 1.0000
8.000 1.1369 0.01619 0.00933 -0.0227 0.0659 1.0000
8.250 1.1497 0.01699 0.01004 -0.0207 0.0492 1.0000
8.500 1.1621 0.01777 0.01073 -0.0186 0.0395 1.0000
8.750 1.1742 0.01853 0.01149 -0.0165 0.0351 1.0000
9.000 1.1860 0.01926 0.01224 -0.0145 0.0325 1.0000
9.250 1.1913 0.02023 0.01324 -0.0114 0.0303 1.0000
9.500 1.2004 0.02093 0.01402 -0.0090 0.0292 1.0000
9.750 1.2087 0.02182 0.01496 -0.0069 0.0281 1.0000
10.000 1.2165 0.02287 0.01607 -0.0050 0.0270 1.0000
10.250 1.2206 0.02428 0.01754 -0.0031 0.0259 1.0000
10.500 1.2212 0.02610 0.01943 -0.0013 0.0250 1.0000
10.750 1.2311 0.02733 0.02074 -0.0004 0.0243 1.0000
11.000 1.2388 0.02879 0.02228 0.0005 0.0236 1.0000
11.250 1.2448 0.03046 0.02402 0.0013 0.0229 1.0000
11.500 1.2495 0.03232 0.02596 0.0020 0.0223 1.0000
11.750 1.2523 0.03444 0.02814 0.0025 0.0218 1.0000
12.000 1.2516 0.03697 0.03073 0.0030 0.0213 1.0000
12.250 1.2462 0.04005 0.03389 0.0036 0.0208 1.0000
12.500 1.2489 0.04243 0.03636 0.0037 0.0205 1.0000
12.750 1.2532 0.04471 0.03874 0.0036 0.0201 1.0000
13.000 1.2563 0.04714 0.04127 0.0035 0.0198 1.0000
13.250 1.2585 0.04969 0.04391 0.0033 0.0193 1.0000
13.500 1.2601 0.05235 0.04666 0.0030 0.0189 1.0000
13.750 1.2613 0.05512 0.04951 0.0026 0.0185 1.0000
14.000 1.2620 0.05798 0.05244 0.0022 0.0182 1.0000
14.250 1.2623 0.06095 0.05546 0.0016 0.0178 1.0000
14.500 1.2619 0.06398 0.05854 0.0011 0.0175 1.0000
14.750 1.2605 0.06701 0.06162 0.0010 0.0172 1.0000
15.000 1.2586 0.06987 0.06454 0.0015 0.0169 1.0000
15.250 1.2578 0.07331 0.06810 0.0004 0.0167 1.0000
15.500 1.2562 0.07687 0.07178 -0.0007 0.0166 1.0000
15.750 1.2539 0.08057 0.07560 -0.0019 0.0164 1.0000
16.000 1.2510 0.08438 0.07954 -0.0031 0.0162 1.0000
16.250 1.2475 0.08836 0.08364 -0.0044 0.0160 1.0000
16.500 1.2433 0.09247 0.08787 -0.0058 0.0158 1.0000
16.750 1.2384 0.09675 0.09227 -0.0073 0.0156 1.0000
17.000 1.2329 0.10122 0.09686 -0.0090 0.0154 1.0000
17.250 1.2269 0.10585 0.10160 -0.0109 0.0153 1.0000
17.500 1.2207 0.11059 0.10645 -0.0129 0.0151 1.0000
17.750 1.2135 0.11558 0.11155 -0.0152 0.0149 1.0000
18.000 1.2058 0.12081 0.11690 -0.0177 0.0148 1.0000
18.250 1.1977 0.12622 0.12241 -0.0203 0.0147 1.0000
18.500 1.1894 0.13180 0.12810 -0.0232 0.0145 1.0000
18.750 1.1813 0.13741 0.13382 -0.0262 0.0144 1.0000
19.000 1.1726 0.14327 0.13978 -0.0294 0.0143 1.0000
19.250 1.1631 0.14943 0.14605 -0.0328 0.0142 1.0000
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