FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 78-K-140 A/20 (fx78k140a20-il) Reynolds number: 500,000 Max Cl/Cd: 118.88 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx78k140a20-il-500000.txt Download as CSV file: xf-fx78k140a20-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-140 A/20
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1040 0.09327 0.08978 -0.1098 0.7499 0.0195
-10.500 -0.1001 0.08949 0.08603 -0.1127 0.7489 0.0203
-10.250 -0.0979 0.08564 0.08220 -0.1144 0.7480 0.0202
-10.000 -0.0932 0.08216 0.07873 -0.1172 0.7471 0.0205
-9.750 -0.0921 0.07820 0.07479 -0.1191 0.7461 0.0205
-9.500 -0.0909 0.07461 0.07121 -0.1207 0.7452 0.0204
-6.750 -0.1992 0.02798 0.02295 -0.1041 0.7315 0.0139
-6.500 -0.1940 0.02426 0.01874 -0.1007 0.7306 0.0135
-6.250 -0.1788 0.02195 0.01605 -0.0987 0.7298 0.0134
-6.000 -0.1585 0.02051 0.01432 -0.0973 0.7289 0.0138
-5.750 -0.1374 0.01946 0.01309 -0.0961 0.7273 0.0142
-5.500 -0.1188 0.01739 0.01081 -0.0947 0.7258 0.0156
-5.250 -0.0962 0.01685 0.01022 -0.0939 0.7244 0.0168
-5.000 -0.0724 0.01652 0.00985 -0.0933 0.7230 0.0190
-4.750 -0.0471 0.01643 0.00970 -0.0930 0.7218 0.0207
-4.500 -0.0272 0.01535 0.00857 -0.0916 0.7206 0.0247
-4.250 -0.0030 0.01501 0.00818 -0.0910 0.7195 0.0278
-4.000 0.0198 0.01452 0.00763 -0.0902 0.7184 0.0332
-3.750 0.0447 0.01428 0.00735 -0.0898 0.7176 0.0393
-3.500 0.0684 0.01393 0.00700 -0.0891 0.7167 0.0485
-3.250 0.0929 0.01367 0.00673 -0.0886 0.7159 0.0600
-3.000 0.1170 0.01350 0.00657 -0.0881 0.7149 0.0760
-2.750 0.1380 0.01338 0.00655 -0.0871 0.7128 0.0984
-2.500 0.1582 0.01311 0.00654 -0.0860 0.7109 0.1573
-2.250 0.1760 0.01260 0.00649 -0.0845 0.7092 0.2838
-2.000 0.1894 0.01185 0.00636 -0.0821 0.7076 0.4650
-1.750 0.1885 0.01083 0.00646 -0.0761 0.7061 0.7534
-1.500 0.2092 0.01115 0.00685 -0.0740 0.7050 0.8420
-1.250 0.2332 0.01134 0.00699 -0.0729 0.7040 0.8625
-1.000 0.2593 0.01147 0.00706 -0.0723 0.7031 0.8741
-0.750 0.2851 0.01156 0.00707 -0.0717 0.7023 0.8834
-0.500 0.3101 0.01174 0.00721 -0.0709 0.7014 0.8942
-0.250 0.3280 0.01206 0.00759 -0.0687 0.6986 0.9060
0.000 0.3475 0.01227 0.00783 -0.0665 0.6963 0.9206
0.250 0.3717 0.01237 0.00793 -0.0652 0.6946 0.9353
0.500 0.4148 0.01249 0.00802 -0.0681 0.6935 0.9468
0.750 0.4522 0.01250 0.00800 -0.0701 0.6923 0.9528
1.000 0.4968 0.01247 0.00792 -0.0739 0.6913 0.9545
1.250 0.5329 0.01237 0.00778 -0.0759 0.6902 0.9555
1.500 0.5667 0.01226 0.00762 -0.0774 0.6892 0.9565
1.750 0.5979 0.01217 0.00749 -0.0784 0.6882 0.9576
2.000 0.6182 0.01225 0.00761 -0.0773 0.6855 0.9600
2.250 0.6191 0.01225 0.00765 -0.0720 0.6821 0.9645
2.500 0.6498 0.01222 0.00763 -0.0731 0.6802 0.9653
2.750 0.6820 0.01211 0.00751 -0.0743 0.6786 0.9659
3.000 0.7157 0.01196 0.00736 -0.0758 0.6772 0.9664
3.250 0.7493 0.01184 0.00723 -0.0773 0.6759 0.9670
3.500 0.7830 0.01174 0.00714 -0.0788 0.6748 0.9676
3.750 0.8104 0.01176 0.00720 -0.0792 0.6723 0.9686
4.000 0.8331 0.01182 0.00734 -0.0786 0.6686 0.9700
4.250 0.8607 0.01175 0.00730 -0.0790 0.6662 0.9711
4.500 0.8878 0.01163 0.00723 -0.0791 0.6643 0.9719
4.750 0.9162 0.01146 0.00707 -0.0795 0.6626 0.9727
5.000 0.9464 0.01129 0.00691 -0.0802 0.6609 0.9732
5.250 0.9641 0.01135 0.00708 -0.0785 0.6570 0.9755
5.500 0.9830 0.01129 0.00709 -0.0770 0.6534 0.9772
5.750 1.0138 0.01118 0.00705 -0.0780 0.6507 0.9776
6.000 1.0486 0.01063 0.00649 -0.0793 0.6458 0.9777
6.250 1.0778 0.01004 0.00594 -0.0795 0.6342 0.9784
6.500 1.1024 0.00961 0.00557 -0.0790 0.6119 0.9796
6.750 1.1258 0.00947 0.00536 -0.0783 0.5773 0.9810
7.000 1.1364 0.01005 0.00561 -0.0755 0.5100 0.9842
7.250 1.1253 0.01196 0.00699 -0.0702 0.4118 0.9907
7.500 1.1018 0.01372 0.00849 -0.0630 0.3580 1.0000
7.750 1.0955 0.01586 0.01048 -0.0605 0.3202 1.0000
8.000 1.0724 0.01922 0.01336 -0.0564 0.2382 1.0000
8.250 1.0569 0.02212 0.01581 -0.0529 0.1593 1.0000
8.500 1.0324 0.02568 0.01872 -0.0487 0.0548 1.0000
8.750 1.0275 0.02806 0.02086 -0.0462 0.0172 1.0000
9.000 1.0392 0.02930 0.02216 -0.0452 0.0132 1.0000
9.250 1.0503 0.03059 0.02353 -0.0442 0.0123 1.0000
9.500 1.0578 0.03216 0.02516 -0.0430 0.0110 1.0000
9.750 1.0604 0.03413 0.02726 -0.0412 0.0103 1.0000
10.000 1.0761 0.03516 0.02834 -0.0409 0.0109 1.0000
10.250 1.0743 0.03764 0.03093 -0.0389 0.0097 1.0000
10.500 1.0808 0.03946 0.03283 -0.0377 0.0096 1.0000
10.750 1.0878 0.04125 0.03470 -0.0365 0.0094 1.0000
11.000 1.1006 0.04256 0.03605 -0.0361 0.0086 1.0000
11.250 1.1065 0.04441 0.03800 -0.0347 0.0088 1.0000
11.500 1.1190 0.04579 0.03938 -0.0343 0.0076 1.0000
11.750 1.1262 0.04754 0.04121 -0.0330 0.0076 1.0000
12.000 1.1351 0.04913 0.04288 -0.0317 0.0075 1.0000
12.250 1.1466 0.05042 0.04426 -0.0302 0.0076 1.0000
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