Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=1
| Details | Polar file |
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Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 56.44 at α=4.75° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-120-050-gn-1000000-n1.txt Download as CSV file: xf-cp-120-050-gn-1000000-n1.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=12% T=5% R=1.1
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.1921 0.09726 0.09399 -0.1894 0.8211 0.0121
-10.500 0.2005 0.09501 0.09173 -0.1903 0.8174 0.0124
-10.250 0.2092 0.09281 0.08952 -0.1912 0.8134 0.0126
-10.000 0.2200 0.09116 0.08785 -0.1920 0.8092 0.0126
-9.750 0.2292 0.08936 0.08603 -0.1926 0.8042 0.0129
-9.500 0.2392 0.08762 0.08427 -0.1933 0.8004 0.0131
-9.250 0.2482 0.08564 0.08228 -0.1940 0.7966 0.0134
-9.000 0.2571 0.08379 0.08042 -0.1945 0.7918 0.0140
-8.750 0.2654 0.08197 0.07858 -0.1949 0.7872 0.0142
-8.500 0.2735 0.08005 0.07664 -0.1953 0.7828 0.0144
-8.250 0.2827 0.07835 0.07494 -0.1957 0.7785 0.0145
-8.000 0.2907 0.07658 0.07316 -0.1959 0.7738 0.0149
-7.750 0.2995 0.07514 0.07170 -0.1959 0.7695 0.0150
-7.500 0.3078 0.07347 0.07002 -0.1960 0.7653 0.0152
-7.250 0.3162 0.07192 0.06847 -0.1960 0.7611 0.0155
-7.000 0.3228 0.07032 0.06687 -0.1957 0.7565 0.0160
-6.750 0.3275 0.06876 0.06529 -0.1950 0.7511 0.0165
-6.500 0.3326 0.06723 0.06376 -0.1943 0.7469 0.0167
-6.250 0.3355 0.06586 0.06239 -0.1930 0.7420 0.0169
-6.000 0.3355 0.06465 0.06119 -0.1910 0.7365 0.0171
-5.750 0.3407 0.06326 0.05979 -0.1903 0.7321 0.0172
-5.500 0.3489 0.06193 0.05847 -0.1900 0.7278 0.0175
-5.250 0.3564 0.06053 0.05706 -0.1896 0.7231 0.0177
-5.000 0.3631 0.05920 0.05572 -0.1889 0.7179 0.0181
-4.750 0.3715 0.05769 0.05421 -0.1887 0.7137 0.0185
-4.500 0.3780 0.05622 0.05275 -0.1880 0.7096 0.0189
-4.250 0.3841 0.05485 0.05137 -0.1870 0.7050 0.0191
-4.000 0.3912 0.05340 0.04992 -0.1863 0.7003 0.0192
-3.750 0.4025 0.05175 0.04826 -0.1865 0.6961 0.0196
-3.500 0.4149 0.05010 0.04660 -0.1869 0.6915 0.0198
-3.250 0.4274 0.04867 0.04516 -0.1869 0.6868 0.0200
-3.000 0.4412 0.04723 0.04371 -0.1871 0.6826 0.0203
-2.750 0.4584 0.04564 0.04210 -0.1881 0.6781 0.0209
-2.500 0.4776 0.04393 0.04037 -0.1895 0.6741 0.0214
-2.250 0.4972 0.04228 0.03869 -0.1908 0.6698 0.0217
-2.000 0.5181 0.04057 0.03695 -0.1923 0.6654 0.0220
-1.750 0.5398 0.03878 0.03510 -0.1940 0.6563 0.0224
-1.500 0.5589 0.03743 0.03369 -0.1946 0.6450 0.0226
-1.250 0.5674 0.03663 0.03276 -0.1925 0.6179 0.0228
-1.000 0.5732 0.03597 0.03190 -0.1899 0.5794 0.0234
-0.750 0.5911 0.03484 0.03065 -0.1900 0.5558 0.0240
-0.500 0.5380 0.03741 0.03235 -0.1747 0.3564 0.0238
-0.250 0.5257 0.03828 0.03264 -0.1686 0.1908 0.0240
0.000 0.5368 0.03800 0.03196 -0.1674 0.0225 0.0243
0.250 0.5710 0.03634 0.03022 -0.1709 0.0208 0.0248
0.500 0.6054 0.03479 0.02858 -0.1742 0.0196 0.0252
0.750 0.6378 0.03357 0.02729 -0.1768 0.0187 0.0255
1.000 0.6690 0.03252 0.02617 -0.1789 0.0188 0.0262
1.250 0.7015 0.03137 0.02494 -0.1813 0.0185 0.0269
1.500 0.7343 0.03019 0.02367 -0.1836 0.0182 0.0274
1.750 0.7677 0.02896 0.02233 -0.1859 0.0177 0.0280
2.000 0.7996 0.02783 0.02110 -0.1877 0.0175 0.0284
2.250 0.8276 0.02710 0.02029 -0.1885 0.0173 0.0287
2.500 0.8568 0.02620 0.01929 -0.1894 0.0171 0.0298
2.750 0.8862 0.02522 0.01819 -0.1904 0.0169 0.0304
3.000 0.9165 0.02405 0.01687 -0.1913 0.0168 0.0310
3.250 0.9457 0.02282 0.01546 -0.1919 0.0166 0.0316
3.500 0.9719 0.02185 0.01430 -0.1918 0.0164 0.0327
3.750 1.0047 0.01830 0.00984 -0.1928 0.0163 0.0356
4.000 1.0239 0.01846 0.00994 -0.1912 0.0161 0.0362
4.250 1.0432 0.01866 0.01008 -0.1896 0.0161 0.0367
4.500 1.0624 0.01889 0.01028 -0.1881 0.0160 0.0369
4.750 1.0814 0.01916 0.01052 -0.1865 0.0160 0.0373
5.000 1.0995 0.01950 0.01084 -0.1847 0.0158 0.0374
5.250 1.1176 0.01985 0.01118 -0.1830 0.0158 0.0376
5.500 1.1357 0.02021 0.01153 -0.1812 0.0157 0.0377
5.750 1.1538 0.02059 0.01191 -0.1795 0.0157 0.0378
6.000 1.1716 0.02100 0.01231 -0.1778 0.0157 0.0379
6.250 1.1886 0.02147 0.01278 -0.1760 0.0157 0.0380
6.500 1.2058 0.02193 0.01325 -0.1742 0.0157 0.0381
6.750 1.2231 0.02240 0.01373 -0.1724 0.0156 0.0383
7.000 1.2402 0.02290 0.01424 -0.1707 0.0155 0.0384
7.250 1.2566 0.02344 0.01480 -0.1688 0.0154 0.0385
7.500 1.2725 0.02403 0.01541 -0.1669 0.0154 0.0386
7.750 1.2890 0.02460 0.01599 -0.1651 0.0153 0.0387
8.000 1.3052 0.02520 0.01661 -0.1633 0.0153 0.0388
8.250 1.3204 0.02586 0.01730 -0.1614 0.0152 0.0389
8.500 1.3357 0.02654 0.01800 -0.1595 0.0152 0.0391
8.750 1.3510 0.02724 0.01872 -0.1577 0.0151 0.0392
9.000 1.3662 0.02795 0.01946 -0.1558 0.0151 0.0393
9.250 1.3805 0.02874 0.02027 -0.1539 0.0150 0.0394
9.500 1.3947 0.02955 0.02112 -0.1520 0.0150 0.0397
9.750 1.4095 0.03034 0.02193 -0.1502 0.0149 0.0399
10.000 1.4233 0.03121 0.02284 -0.1483 0.0148 0.0402
10.250 1.4365 0.03215 0.02381 -0.1464 0.0148 0.0403
10.500 1.4505 0.03303 0.02472 -0.1446 0.0148 0.0405
10.750 1.4635 0.03401 0.02574 -0.1428 0.0147 0.0408
11.000 1.4761 0.03504 0.02681 -0.1409 0.0146 0.0412
11.250 1.4889 0.03607 0.02788 -0.1391 0.0146 0.0416
11.500 1.5019 0.03710 0.02895 -0.1374 0.0144 0.0419
11.750 1.5140 0.03822 0.03011 -0.1356 0.0143 0.0424
12.000 1.5263 0.03934 0.03128 -0.1338 0.0141 0.0437
12.250 1.5385 0.04049 0.03248 -0.1321 0.0140 0.0451
12.500 1.5500 0.04171 0.03374 -0.1304 0.0138 0.0460
12.750 1.5611 0.04299 0.03507 -0.1287 0.0138 0.0472
13.000 1.5730 0.04422 0.03635 -0.1270 0.0136 0.0515
13.250 1.6110 0.04559 0.03883 -0.1315 0.0135 1.0000
13.500 1.6206 0.04701 0.04029 -0.1296 0.0134 1.0000
13.750 1.6301 0.04844 0.04175 -0.1278 0.0133 1.0000
14.000 1.6404 0.04981 0.04315 -0.1261 0.0132 1.0000
14.250 1.6488 0.05138 0.04477 -0.1244 0.0131 1.0000
14.500 1.6584 0.05285 0.04627 -0.1227 0.0130 1.0000
14.750 1.6681 0.05433 0.04779 -0.1211 0.0130 1.0000
15.000 1.6765 0.05596 0.04947 -0.1195 0.0129 1.0000
15.250 1.6860 0.05749 0.05103 -0.1180 0.0128 1.0000
15.500 1.6944 0.05915 0.05273 -0.1165 0.0128 1.0000
15.750 1.7027 0.06082 0.05445 -0.1150 0.0127 1.0000
16.000 1.7113 0.06248 0.05615 -0.1136 0.0127 1.0000
16.250 1.7192 0.06425 0.05797 -0.1122 0.0126 1.0000
16.500 1.7255 0.06621 0.05999 -0.1107 0.0126 1.0000
16.750 1.7333 0.06800 0.06184 -0.1094 0.0125 1.0000
17.000 1.7398 0.06999 0.06387 -0.1081 0.0125 1.0000
17.250 1.7462 0.07199 0.06595 -0.1068 0.0124 1.0000
17.500 1.7535 0.07389 0.06790 -0.1057 0.0124 1.0000
17.750 1.7590 0.07604 0.07012 -0.1045 0.0123 1.0000
18.000 1.7654 0.07810 0.07224 -0.1035 0.0123 1.0000
18.250 1.7718 0.08016 0.07436 -0.1024 0.0122 1.0000
18.500 1.7770 0.08240 0.07668 -0.1015 0.0121 1.0000
18.750 1.7828 0.08458 0.07893 -0.1006 0.0120 1.0000
19.000 1.7891 0.08671 0.08112 -0.0998 0.0120 1.0000
19.250 1.7936 0.08908 0.08356 -0.0990 0.0118 1.0000
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Polar data table (+)
Polar graphs
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