CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.44 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkyh-il-1000000.txt Download as CSV file: xf-clarkyh-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.9832 0.11524 0.11317 -0.0055 1.0000 0.0148
-18.000 -1.0617 0.09714 0.09486 -0.0171 1.0000 0.0145
-17.750 -1.1447 0.07996 0.07747 -0.0289 1.0000 0.0140
-17.500 -1.2249 0.06269 0.05996 -0.0414 1.0000 0.0135
-17.250 -1.2825 0.04327 0.04012 -0.0607 1.0000 0.0132
-17.000 -1.2985 0.03832 0.03497 -0.0632 1.0000 0.0132
-16.750 -1.3121 0.03481 0.03130 -0.0629 1.0000 0.0133
-16.500 -1.3242 0.03200 0.02832 -0.0608 1.0000 0.0135
-16.250 -1.3286 0.02998 0.02618 -0.0581 1.0000 0.0138
-16.000 -1.3255 0.02848 0.02459 -0.0555 1.0000 0.0141
-15.750 -1.3154 0.02727 0.02328 -0.0535 1.0000 0.0144
-15.500 -1.3016 0.02621 0.02214 -0.0519 1.0000 0.0148
-15.250 -1.2861 0.02524 0.02108 -0.0503 1.0000 0.0152
-15.000 -1.2693 0.02432 0.02007 -0.0489 1.0000 0.0156
-14.750 -1.2513 0.02346 0.01911 -0.0475 1.0000 0.0159
-14.500 -1.2319 0.02271 0.01825 -0.0462 1.0000 0.0162
-14.250 -1.2178 0.02138 0.01682 -0.0444 1.0000 0.0169
-14.000 -1.1986 0.02052 0.01590 -0.0431 1.0000 0.0175
-13.750 -1.1775 0.01984 0.01516 -0.0420 1.0000 0.0181
-13.500 -1.1555 0.01922 0.01448 -0.0410 1.0000 0.0187
-13.250 -1.1329 0.01864 0.01383 -0.0400 1.0000 0.0193
-13.000 -1.1106 0.01801 0.01312 -0.0389 1.0000 0.0199
-12.750 -1.0891 0.01726 0.01234 -0.0378 1.0000 0.0210
-12.500 -1.0649 0.01682 0.01188 -0.0371 1.0000 0.0219
-12.250 -1.0402 0.01642 0.01144 -0.0363 1.0000 0.0229
-12.000 -1.0104 0.01599 0.01094 -0.0366 0.9868 0.0237
-11.750 -0.9799 0.01541 0.01035 -0.0372 0.9698 0.0253
-11.500 -0.9535 0.01518 0.01008 -0.0366 0.9524 0.0264
-11.250 -0.9298 0.01498 0.00980 -0.0353 0.9367 0.0274
-11.000 -0.9063 0.01474 0.00946 -0.0341 0.9237 0.0284
-10.750 -0.8821 0.01445 0.00916 -0.0331 0.9127 0.0298
-10.500 -0.8558 0.01439 0.00907 -0.0324 0.9038 0.0310
-10.250 -0.8295 0.01430 0.00893 -0.0317 0.8959 0.0321
-10.000 -0.8027 0.01419 0.00876 -0.0311 0.8899 0.0331
-9.750 -0.7778 0.01377 0.00827 -0.0303 0.8833 0.0342
-9.250 -0.7245 0.01350 0.00796 -0.0292 0.8706 0.0364
-9.000 -0.6975 0.01338 0.00781 -0.0287 0.8648 0.0376
-8.750 -0.6706 0.01325 0.00760 -0.0282 0.8595 0.0386
-8.500 -0.6429 0.01317 0.00749 -0.0278 0.8539 0.0393
-8.250 -0.6181 0.01264 0.00688 -0.0270 0.8479 0.0406
-8.000 -0.5926 0.01223 0.00644 -0.0264 0.8419 0.0418
-7.750 -0.5658 0.01197 0.00618 -0.0259 0.8357 0.0429
-7.500 -0.5390 0.01178 0.00594 -0.0254 0.8298 0.0441
-7.250 -0.5119 0.01156 0.00568 -0.0250 0.8243 0.0451
-7.000 -0.4846 0.01136 0.00545 -0.0246 0.8182 0.0461
-6.750 -0.4572 0.01123 0.00526 -0.0242 0.8123 0.0468
-6.500 -0.4299 0.01100 0.00500 -0.0238 0.8061 0.0474
-6.250 -0.4053 0.01036 0.00430 -0.0230 0.7992 0.0493
-6.000 -0.3787 0.01006 0.00397 -0.0225 0.7924 0.0504
-5.750 -0.3516 0.00980 0.00369 -0.0221 0.7843 0.0516
-5.500 -0.3245 0.00959 0.00344 -0.0217 0.7760 0.0527
-5.250 -0.2972 0.00939 0.00319 -0.0214 0.7658 0.0536
-5.000 -0.2699 0.00921 0.00296 -0.0210 0.7527 0.0545
-4.750 -0.2427 0.00906 0.00274 -0.0206 0.7336 0.0553
-4.500 -0.2155 0.00897 0.00256 -0.0202 0.7088 0.0560
-4.250 -0.1888 0.00884 0.00231 -0.0198 0.6835 0.0576
-4.000 -0.1618 0.00873 0.00212 -0.0194 0.6633 0.0596
-3.750 -0.1346 0.00865 0.00198 -0.0191 0.6473 0.0617
-3.500 -0.1073 0.00858 0.00186 -0.0188 0.6333 0.0641
-3.250 -0.0800 0.00850 0.00176 -0.0185 0.6201 0.0703
-3.000 -0.0531 0.00833 0.00168 -0.0182 0.6095 0.0949
-2.750 -0.0256 0.00827 0.00160 -0.0180 0.6002 0.1068
-2.500 0.0017 0.00814 0.00151 -0.0178 0.5912 0.1223
-2.250 0.0280 0.00793 0.00149 -0.0174 0.5823 0.1813
-2.000 0.0560 0.00791 0.00148 -0.0173 0.5721 0.1933
-1.750 0.0841 0.00791 0.00146 -0.0173 0.5613 0.2012
-1.500 0.1119 0.00791 0.00144 -0.0172 0.5494 0.2074
-1.250 0.1398 0.00791 0.00142 -0.0171 0.5366 0.2141
-1.000 0.1678 0.00794 0.00141 -0.0171 0.5222 0.2185
-0.750 0.1954 0.00795 0.00139 -0.0170 0.5073 0.2245
-0.500 0.2231 0.00797 0.00139 -0.0169 0.4930 0.2303
-0.250 0.2508 0.00801 0.00140 -0.0169 0.4802 0.2354
0.000 0.2783 0.00804 0.00141 -0.0168 0.4692 0.2427
0.250 0.3059 0.00806 0.00143 -0.0167 0.4595 0.2504
0.500 0.3333 0.00806 0.00145 -0.0167 0.4511 0.2655
0.750 0.3587 0.00788 0.00149 -0.0163 0.4424 0.3431
1.000 0.3793 0.00726 0.00151 -0.0152 0.4344 0.5622
1.250 0.3910 0.00640 0.00155 -0.0117 0.4272 0.8521
1.500 0.4236 0.00632 0.00171 -0.0125 0.4195 0.9265
1.750 0.4706 0.00653 0.00191 -0.0167 0.4091 0.9582
2.000 0.5024 0.00667 0.00204 -0.0175 0.4013 0.9710
2.250 0.5412 0.00685 0.00217 -0.0200 0.3906 0.9755
2.500 0.5743 0.00700 0.00228 -0.0213 0.3792 0.9809
2.750 0.6102 0.00718 0.00240 -0.0232 0.3620 0.9846
3.000 0.6471 0.00752 0.00254 -0.0255 0.3131 0.9871
3.250 0.6787 0.00829 0.00291 -0.0271 0.2370 0.9900
3.500 0.7118 0.00859 0.00313 -0.0286 0.2236 0.9927
3.750 0.7506 0.00878 0.00330 -0.0313 0.2169 0.9949
4.000 0.7877 0.00903 0.00349 -0.0337 0.2075 0.9966
4.250 0.8226 0.00914 0.00362 -0.0355 0.2033 0.9980
4.500 0.8575 0.00932 0.00377 -0.0375 0.1974 0.9994
4.750 0.8866 0.00953 0.00395 -0.0381 0.1912 1.0000
5.000 0.9110 0.00963 0.00408 -0.0377 0.1880 1.0000
5.250 0.9350 0.00978 0.00422 -0.0373 0.1836 1.0000
5.500 0.9583 0.01000 0.00441 -0.0367 0.1761 1.0000
5.750 0.9826 0.01012 0.00455 -0.0363 0.1707 1.0000
6.000 1.0058 0.01035 0.00474 -0.0358 0.1625 1.0000
6.250 1.0290 0.01056 0.00492 -0.0353 0.1511 1.0000
6.500 1.0499 0.01099 0.00520 -0.0344 0.1241 1.0000
6.750 1.0650 0.01188 0.00582 -0.0328 0.0823 1.0000
7.000 1.0847 0.01234 0.00623 -0.0317 0.0735 1.0000
7.250 1.1055 0.01268 0.00658 -0.0308 0.0667 1.0000
7.500 1.1241 0.01317 0.00701 -0.0296 0.0542 1.0000
7.750 1.1391 0.01390 0.00758 -0.0278 0.0348 1.0000
8.000 1.1564 0.01444 0.00809 -0.0264 0.0294 1.0000
8.250 1.1736 0.01495 0.00859 -0.0249 0.0268 1.0000
8.500 1.1903 0.01547 0.00913 -0.0234 0.0248 1.0000
8.750 1.2079 0.01590 0.00960 -0.0221 0.0236 1.0000
9.000 1.2238 0.01641 0.01013 -0.0205 0.0223 1.0000
9.250 1.2361 0.01711 0.01086 -0.0184 0.0209 1.0000
9.500 1.2516 0.01758 0.01137 -0.0168 0.0202 1.0000
9.750 1.2661 0.01808 0.01192 -0.0151 0.0195 1.0000
10.000 1.2767 0.01862 0.01250 -0.0127 0.0188 1.0000
10.250 1.2859 0.01926 0.01317 -0.0103 0.0182 1.0000
10.500 1.2940 0.02013 0.01408 -0.0082 0.0175 1.0000
10.750 1.2979 0.02141 0.01543 -0.0059 0.0169 1.0000
11.000 1.3113 0.02219 0.01628 -0.0049 0.0166 1.0000
11.250 1.3235 0.02312 0.01727 -0.0040 0.0161 1.0000
11.500 1.3350 0.02415 0.01835 -0.0031 0.0157 1.0000
11.750 1.3459 0.02527 0.01952 -0.0024 0.0152 1.0000
12.000 1.3557 0.02653 0.02083 -0.0016 0.0148 1.0000
12.250 1.3629 0.02807 0.02242 -0.0009 0.0144 1.0000
12.500 1.3650 0.03011 0.02453 -0.0002 0.0140 1.0000
12.750 1.3592 0.03303 0.02756 0.0006 0.0137 1.0000
13.000 1.3670 0.03476 0.02937 0.0007 0.0135 1.0000
13.250 1.3731 0.03674 0.03143 0.0007 0.0133 1.0000
13.500 1.3777 0.03895 0.03372 0.0006 0.0131 1.0000
13.750 1.3804 0.04141 0.03626 0.0004 0.0129 1.0000
14.000 1.3820 0.04406 0.03899 0.0000 0.0127 1.0000
14.250 1.3825 0.04687 0.04189 -0.0004 0.0124 1.0000
14.500 1.3817 0.04986 0.04496 -0.0009 0.0123 1.0000
14.750 1.3804 0.05302 0.04820 -0.0015 0.0121 1.0000
15.000 1.3778 0.05642 0.05168 -0.0023 0.0119 1.0000
15.250 1.3740 0.06003 0.05538 -0.0032 0.0118 1.0000
15.500 1.3694 0.06386 0.05928 -0.0042 0.0116 1.0000
15.750 1.3630 0.06797 0.06348 -0.0054 0.0115 1.0000
16.000 1.3540 0.07251 0.06810 -0.0067 0.0113 1.0000
16.250 1.3431 0.07739 0.07307 -0.0082 0.0112 1.0000
16.500 1.3294 0.08270 0.07848 -0.0097 0.0110 1.0000
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