FX 78-K-150/20 (fx78k150-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 78-K-150/20 (fx78k150-il) Reynolds number: 1,000,000 Max Cl/Cd: 143.4 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx78k150-il-1000000.txt Download as CSV file: xf-fx78k150-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-150/20
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5642 0.04454 0.04130 -0.1202 0.7238 0.0073
-13.000 -0.5789 0.03884 0.03541 -0.1256 0.7227 0.0075
-12.750 -0.5836 0.03565 0.03209 -0.1274 0.7217 0.0076
-12.500 -0.5847 0.03313 0.02941 -0.1279 0.7203 0.0077
-12.250 -0.6083 0.02900 0.02491 -0.1258 0.7192 0.0075
-12.000 -0.6088 0.02720 0.02293 -0.1237 0.7184 0.0073
-11.750 -0.6094 0.02555 0.02111 -0.1209 0.7175 0.0072
-11.500 -0.6082 0.02431 0.01979 -0.1179 0.7165 0.0077
-11.250 -0.6110 0.02282 0.01809 -0.1137 0.7155 0.0076
-11.000 -0.5914 0.02288 0.01820 -0.1128 0.7144 0.0081
-10.750 -0.5816 0.02184 0.01703 -0.1105 0.7132 0.0082
-10.500 -0.5684 0.02099 0.01605 -0.1086 0.7121 0.0084
-10.250 -0.5529 0.02029 0.01524 -0.1070 0.7110 0.0087
-10.000 -0.5370 0.01952 0.01433 -0.1055 0.7101 0.0088
-9.750 -0.5224 0.01853 0.01318 -0.1037 0.7091 0.0090
-9.500 -0.5044 0.01782 0.01235 -0.1023 0.7081 0.0094
-9.250 -0.4856 0.01715 0.01156 -0.1011 0.7071 0.0096
-9.000 -0.4664 0.01652 0.01081 -0.0999 0.7060 0.0097
-8.750 -0.4495 0.01564 0.00978 -0.0984 0.7049 0.0101
-8.500 -0.4301 0.01500 0.00911 -0.0972 0.7042 0.0111
-8.250 -0.4082 0.01457 0.00864 -0.0965 0.7034 0.0115
-8.000 -0.3856 0.01418 0.00819 -0.0957 0.7024 0.0123
-7.750 -0.3620 0.01389 0.00785 -0.0952 0.7013 0.0129
-7.500 -0.3400 0.01342 0.00730 -0.0943 0.7003 0.0131
-7.250 -0.3196 0.01279 0.00662 -0.0932 0.6994 0.0147
-7.000 -0.2953 0.01254 0.00635 -0.0928 0.6984 0.0160
-6.750 -0.2708 0.01230 0.00606 -0.0924 0.6975 0.0171
-6.500 -0.2474 0.01194 0.00565 -0.0917 0.6965 0.0185
-6.250 -0.2235 0.01163 0.00534 -0.0912 0.6955 0.0209
-6.000 -0.1986 0.01140 0.00506 -0.0909 0.6946 0.0227
-5.750 -0.1742 0.01114 0.00478 -0.0904 0.6935 0.0257
-5.500 -0.1491 0.01096 0.00459 -0.0901 0.6926 0.0286
-5.250 -0.1232 0.01090 0.00450 -0.0900 0.6914 0.0305
-5.000 -0.0994 0.01064 0.00424 -0.0894 0.6905 0.0351
-4.750 -0.0741 0.01047 0.00408 -0.0891 0.6898 0.0384
-4.500 -0.0487 0.01032 0.00391 -0.0888 0.6889 0.0415
-4.250 -0.0240 0.01010 0.00372 -0.0884 0.6878 0.0476
-4.000 0.0022 0.01001 0.00362 -0.0883 0.6868 0.0513
-3.750 0.0269 0.00979 0.00344 -0.0879 0.6858 0.0602
-3.500 0.0527 0.00967 0.00331 -0.0877 0.6848 0.0673
-3.250 0.0782 0.00951 0.00319 -0.0874 0.6838 0.0773
-3.000 0.1033 0.00933 0.00306 -0.0871 0.6827 0.0961
-2.750 0.1281 0.00911 0.00294 -0.0868 0.6817 0.1251
-2.500 0.1520 0.00886 0.00283 -0.0863 0.6806 0.1703
-2.250 0.1753 0.00859 0.00275 -0.0857 0.6797 0.2295
-2.000 0.1966 0.00825 0.00267 -0.0847 0.6787 0.3146
-1.750 0.2164 0.00791 0.00264 -0.0834 0.6776 0.4137
-1.500 0.2306 0.00742 0.00260 -0.0810 0.6764 0.5576
-1.250 0.2379 0.00679 0.00259 -0.0767 0.6754 0.7325
-1.000 0.2582 0.00676 0.00276 -0.0750 0.6743 0.7996
-0.750 0.2835 0.00683 0.00282 -0.0745 0.6732 0.8182
-0.500 0.3090 0.00691 0.00289 -0.0740 0.6721 0.8306
-0.250 0.3347 0.00698 0.00295 -0.0737 0.6709 0.8397
0.000 0.3613 0.00704 0.00300 -0.0735 0.6697 0.8468
0.250 0.3875 0.00709 0.00303 -0.0732 0.6685 0.8542
0.500 0.4145 0.00716 0.00311 -0.0731 0.6674 0.8619
0.750 0.4410 0.00720 0.00314 -0.0728 0.6663 0.8684
1.000 0.4685 0.00728 0.00323 -0.0728 0.6652 0.8762
1.250 0.4948 0.00736 0.00331 -0.0725 0.6640 0.8841
1.500 0.5219 0.00749 0.00345 -0.0725 0.6625 0.8900
1.750 0.5457 0.00753 0.00351 -0.0717 0.6614 0.8955
2.000 0.5729 0.00750 0.00351 -0.0718 0.6601 0.8984
2.250 0.6000 0.00749 0.00352 -0.0719 0.6585 0.9003
2.500 0.6272 0.00748 0.00352 -0.0720 0.6569 0.9017
2.750 0.6546 0.00746 0.00351 -0.0722 0.6552 0.9030
3.000 0.6823 0.00745 0.00350 -0.0724 0.6538 0.9042
3.250 0.7100 0.00744 0.00349 -0.0727 0.6523 0.9056
3.500 0.7377 0.00744 0.00348 -0.0729 0.6507 0.9068
3.750 0.7657 0.00751 0.00354 -0.0733 0.6486 0.9077
4.000 0.7904 0.00750 0.00359 -0.0729 0.6469 0.9089
4.250 0.8161 0.00749 0.00362 -0.0728 0.6449 0.9101
4.500 0.8434 0.00748 0.00365 -0.0730 0.6430 0.9112
4.750 0.8712 0.00747 0.00367 -0.0733 0.6410 0.9122
5.000 0.8997 0.00731 0.00350 -0.0736 0.6362 0.9133
5.250 0.9241 0.00719 0.00345 -0.0731 0.6295 0.9147
5.500 0.9500 0.00709 0.00334 -0.0729 0.6225 0.9159
5.750 0.9741 0.00703 0.00334 -0.0724 0.6123 0.9171
6.000 0.9987 0.00704 0.00336 -0.0720 0.6018 0.9184
6.250 1.0196 0.00711 0.00341 -0.0709 0.5814 0.9202
6.500 1.0335 0.00745 0.00361 -0.0684 0.5435 0.9221
6.750 1.0304 0.00854 0.00435 -0.0633 0.4708 0.9248
7.000 1.0224 0.01168 0.00690 -0.0611 0.3451 0.9288
7.250 1.0075 0.01679 0.01134 -0.0620 0.2091 0.9334
7.500 0.9897 0.02008 0.01414 -0.0588 0.1127 0.9379
7.750 0.9822 0.02266 0.01636 -0.0564 0.0377 0.9419
8.000 0.9914 0.02407 0.01769 -0.0554 0.0190 0.9454
8.250 1.0044 0.02522 0.01886 -0.0546 0.0144 0.9491
8.500 1.0224 0.02604 0.01972 -0.0545 0.0134 0.9531
8.750 1.0401 0.02700 0.02073 -0.0544 0.0123 0.9591
9.000 1.0533 0.02845 0.02226 -0.0543 0.0107 0.9690
9.250 1.0723 0.02986 0.02371 -0.0546 0.0099 1.0000
9.500 1.0858 0.03101 0.02490 -0.0539 0.0097 1.0000
9.750 1.0974 0.03231 0.02625 -0.0531 0.0097 1.0000
10.000 1.1129 0.03332 0.02727 -0.0527 0.0088 1.0000
10.250 1.1232 0.03475 0.02873 -0.0517 0.0081 1.0000
10.500 1.1325 0.03629 0.03036 -0.0507 0.0087 1.0000
10.750 1.1463 0.03744 0.03152 -0.0502 0.0082 1.0000
11.000 1.1392 0.04027 0.03444 -0.0478 0.0073 1.0000
11.250 1.1473 0.04192 0.03614 -0.0467 0.0073 1.0000
11.500 1.1547 0.04358 0.03786 -0.0455 0.0073 1.0000
11.750 1.1693 0.04473 0.03904 -0.0451 0.0071 1.0000
12.000 1.1847 0.04583 0.04018 -0.0449 0.0068 1.0000
12.250 1.1861 0.04793 0.04236 -0.0428 0.0069 1.0000
12.500 1.2001 0.04916 0.04364 -0.0425 0.0066 1.0000
12.750 1.2139 0.05044 0.04495 -0.0423 0.0063 1.0000
13.000 1.2191 0.05209 0.04669 -0.0402 0.0066 1.0000
13.250 1.2305 0.05354 0.04819 -0.0397 0.0063 1.0000
13.500 1.2419 0.05507 0.04976 -0.0394 0.0059 1.0000
13.750 1.2519 0.05637 0.05115 -0.0377 0.0060 1.0000
14.000 1.2619 0.05808 0.05289 -0.0376 0.0057 1.0000
14.250 1.2710 0.05980 0.05466 -0.0371 0.0055 1.0000
14.500 1.2793 0.06139 0.05631 -0.0359 0.0053 1.0000
14.750 1.2895 0.06289 0.05795 -0.0347 0.0054 1.0000
15.000 1.3004 0.06435 0.05957 -0.0330 0.0056 1.0000
15.250 1.2977 0.06744 0.06286 -0.0311 0.0049 1.0000
15.750 1.3001 0.07309 0.06883 -0.0292 0.0049 1.0000
16.000 1.3113 0.07466 0.07040 -0.0292 0.0052 1.0000
16.250 1.2984 0.07935 0.07536 -0.0288 0.0049 1.0000
16.750 1.2661 0.09025 0.08677 -0.0275 0.0049 1.0000
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