FX 78-K-140/20 (fx78k140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 78-K-140/20 (fx78k140-il) Reynolds number: 1,000,000 Max Cl/Cd: 162.48 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx78k140-il-1000000.txt Download as CSV file: xf-fx78k140-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-140/20
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1116 0.08256 0.07996 -0.0730 0.7227 0.0080
-10.500 -0.1146 0.07772 0.07515 -0.0747 0.7222 0.0092
-10.250 -0.1135 0.07409 0.07152 -0.0760 0.7216 0.0080
-10.000 -0.1162 0.06961 0.06706 -0.0775 0.7210 0.0083
-9.750 -0.2121 0.07915 0.07642 -0.0812 0.7236 0.0058
-9.500 -0.2232 0.07204 0.06937 -0.0857 0.7230 0.0060
-8.500 -0.4699 0.02151 0.01709 -0.0774 0.7178 0.0045
-8.250 -0.4272 0.02418 0.02013 -0.0800 0.7168 0.0051
-8.000 -0.4364 0.01923 0.01445 -0.0742 0.7156 0.0048
-7.750 -0.3989 0.02130 0.01681 -0.0763 0.7146 0.0056
-7.500 -0.3861 0.01936 0.01456 -0.0739 0.7136 0.0058
-7.250 -0.3683 0.01806 0.01302 -0.0722 0.7127 0.0062
-7.000 -0.3462 0.01748 0.01231 -0.0714 0.7117 0.0063
-6.750 -0.3329 0.01524 0.00969 -0.0690 0.7104 0.0072
-6.500 -0.3112 0.01445 0.00877 -0.0680 0.7095 0.0074
-6.250 -0.2862 0.01425 0.00857 -0.0677 0.7086 0.0079
-6.000 -0.2613 0.01399 0.00828 -0.0673 0.7076 0.0088
-5.750 -0.2372 0.01353 0.00775 -0.0667 0.7066 0.0095
-5.500 -0.2104 0.01357 0.00778 -0.0667 0.7055 0.0102
-5.250 -0.1862 0.01305 0.00717 -0.0661 0.7045 0.0103
-5.000 -0.1686 0.01166 0.00559 -0.0641 0.7033 0.0115
-4.750 -0.1433 0.01142 0.00535 -0.0638 0.7022 0.0130
-4.500 -0.1195 0.01100 0.00483 -0.0631 0.7012 0.0134
-4.250 -0.0939 0.01077 0.00457 -0.0627 0.7003 0.0155
-4.000 -0.0690 0.01049 0.00423 -0.0623 0.6994 0.0169
-3.750 -0.0455 0.01009 0.00379 -0.0615 0.6984 0.0210
-3.500 -0.0198 0.00996 0.00362 -0.0611 0.6973 0.0242
-3.250 0.0048 0.00974 0.00341 -0.0606 0.6961 0.0317
-3.000 0.0302 0.00955 0.00324 -0.0603 0.6952 0.0408
-2.750 0.0557 0.00939 0.00311 -0.0600 0.6941 0.0521
-2.500 0.0814 0.00924 0.00300 -0.0597 0.6929 0.0645
-2.250 0.1067 0.00906 0.00289 -0.0594 0.6916 0.0836
-2.000 0.1314 0.00884 0.00278 -0.0590 0.6904 0.1182
-1.750 0.1550 0.00854 0.00267 -0.0583 0.6892 0.1811
-1.500 0.1768 0.00814 0.00258 -0.0574 0.6880 0.2783
-1.250 0.1966 0.00767 0.00249 -0.0561 0.6869 0.4062
-1.000 0.2030 0.00674 0.00238 -0.0519 0.6858 0.6624
-0.750 0.2163 0.00635 0.00239 -0.0487 0.6845 0.7937
-0.500 0.2405 0.00630 0.00247 -0.0480 0.6831 0.8472
-0.250 0.2685 0.00626 0.00248 -0.0481 0.6821 0.8730
0.000 0.2984 0.00623 0.00250 -0.0487 0.6809 0.8921
0.250 0.3359 0.00621 0.00253 -0.0509 0.6796 0.9193
0.500 0.3737 0.00622 0.00254 -0.0533 0.6783 0.9309
0.750 0.4202 0.00628 0.00261 -0.0576 0.6770 0.9465
1.000 0.4618 0.00633 0.00264 -0.0607 0.6755 0.9553
1.250 0.5067 0.00644 0.00272 -0.0645 0.6739 0.9608
1.500 0.5344 0.00648 0.00274 -0.0646 0.6724 0.9668
1.750 0.5709 0.00653 0.00276 -0.0668 0.6709 0.9677
2.000 0.6064 0.00661 0.00282 -0.0687 0.6691 0.9686
2.250 0.6425 0.00664 0.00287 -0.0708 0.6673 0.9699
2.500 0.6767 0.00666 0.00291 -0.0726 0.6653 0.9712
2.750 0.7103 0.00668 0.00294 -0.0741 0.6634 0.9728
3.000 0.7431 0.00668 0.00295 -0.0755 0.6613 0.9747
3.250 0.7736 0.00669 0.00296 -0.0764 0.6594 0.9776
3.500 0.8037 0.00671 0.00297 -0.0772 0.6571 0.9801
3.750 0.8383 0.00676 0.00304 -0.0791 0.6552 0.9810
4.000 0.8725 0.00678 0.00311 -0.0808 0.6528 0.9822
4.250 0.9062 0.00679 0.00318 -0.0825 0.6502 0.9837
4.500 0.9391 0.00679 0.00321 -0.0840 0.6476 0.9855
4.750 0.9708 0.00677 0.00317 -0.0851 0.6428 0.9877
5.000 1.0020 0.00677 0.00325 -0.0862 0.6378 0.9899
5.250 1.0364 0.00673 0.00324 -0.0880 0.6309 0.9911
5.500 1.0697 0.00669 0.00320 -0.0896 0.6153 0.9927
5.750 1.1016 0.00678 0.00326 -0.0909 0.5896 0.9947
6.000 1.1235 0.00791 0.00389 -0.0912 0.4867 0.9985
6.250 1.1309 0.00932 0.00487 -0.0888 0.4027 1.0000
6.500 1.1203 0.01052 0.00578 -0.0827 0.3456 1.0000
6.750 1.0956 0.01196 0.00698 -0.0743 0.2973 1.0000
7.000 1.0600 0.01373 0.00857 -0.0646 0.2598 1.0000
7.250 1.0488 0.01531 0.00996 -0.0594 0.2203 1.0000
7.500 1.0246 0.01784 0.01205 -0.0532 0.1441 1.0000
7.750 1.0215 0.01947 0.01345 -0.0499 0.0990 1.0000
8.000 1.0045 0.02201 0.01558 -0.0452 0.0222 1.0000
8.250 1.0099 0.02333 0.01685 -0.0429 0.0078 1.0000
8.500 1.0214 0.02431 0.01788 -0.0415 0.0070 1.0000
8.750 1.0316 0.02538 0.01900 -0.0401 0.0056 1.0000
9.000 1.0478 0.02609 0.01973 -0.0392 0.0065 1.0000
9.250 1.0489 0.02785 0.02163 -0.0367 0.0056 1.0000
9.500 1.0662 0.02854 0.02232 -0.0361 0.0050 1.0000
9.750 1.0786 0.02957 0.02339 -0.0351 0.0045 1.0000
10.000 1.0876 0.03089 0.02474 -0.0338 0.0038 1.0000
10.250 1.0959 0.03231 0.02629 -0.0323 0.0044 1.0000
10.500 1.1027 0.03387 0.02787 -0.0309 0.0037 1.0000
10.750 1.1041 0.03586 0.02995 -0.0290 0.0035 1.0000
11.000 1.1137 0.03727 0.03142 -0.0278 0.0036 1.0000
11.250 1.1185 0.03907 0.03330 -0.0262 0.0036 1.0000
11.500 1.1297 0.04036 0.03465 -0.0253 0.0038 1.0000
11.750 1.1336 0.04223 0.03658 -0.0238 0.0036 1.0000
12.000 1.1369 0.04412 0.03857 -0.0217 0.0037 1.0000
12.250 1.1477 0.04546 0.03998 -0.0207 0.0038 1.0000
12.500 1.1584 0.04680 0.04139 -0.0196 0.0038 1.0000
12.750 1.1666 0.04829 0.04292 -0.0181 0.0036 1.0000
13.000 1.1800 0.04935 0.04405 -0.0157 0.0033 1.0000
13.250 1.1916 0.05077 0.04557 -0.0147 0.0033 1.0000
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