FX 78-K-140/20 (fx78k140-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 78-K-140/20 (fx78k140-il) Reynolds number: 200,000 Max Cl/Cd: 53.83 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx78k140-il-200000-n5.txt Download as CSV file: xf-fx78k140-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1843 0.09416 0.08972 -0.0801 0.7545 0.0135
-10.000 -0.1853 0.09012 0.08571 -0.0817 0.7535 0.0132
-9.750 -0.1884 0.08580 0.08143 -0.0835 0.7525 0.0133
-9.500 -0.1920 0.08160 0.07725 -0.0853 0.7516 0.0131
-9.250 -0.1949 0.07779 0.07347 -0.0870 0.7502 0.0126
-9.000 -0.2033 0.07315 0.06892 -0.0894 0.7483 0.0124
-8.750 -0.2180 0.06775 0.06361 -0.0931 0.7464 0.0120
-8.500 -0.2336 0.06337 0.05925 -0.0948 0.7445 0.0121
-8.250 -0.2589 0.05855 0.05437 -0.0935 0.7428 0.0116
-8.000 -0.2734 0.05388 0.04958 -0.0923 0.7413 0.0114
-7.750 -0.2919 0.04745 0.04286 -0.0897 0.7399 0.0111
-7.500 -0.3016 0.04228 0.03734 -0.0866 0.7386 0.0111
-7.250 -0.2979 0.03967 0.03447 -0.0844 0.7376 0.0116
-7.000 -0.2990 0.03544 0.02981 -0.0811 0.7355 0.0115
-6.750 -0.2884 0.03345 0.02754 -0.0792 0.7336 0.0123
-6.500 -0.2787 0.03064 0.02429 -0.0768 0.7319 0.0126
-6.250 -0.2626 0.02896 0.02227 -0.0751 0.7302 0.0136
-6.000 -0.2441 0.02740 0.02031 -0.0736 0.7288 0.0153
-5.750 -0.2243 0.02577 0.01830 -0.0723 0.7275 0.0158
-5.500 -0.2041 0.02366 0.01583 -0.0710 0.7264 0.0168
-5.250 -0.1818 0.02247 0.01446 -0.0702 0.7254 0.0180
-5.000 -0.1582 0.02162 0.01348 -0.0695 0.7246 0.0193
-4.750 -0.1340 0.02106 0.01276 -0.0690 0.7238 0.0217
-4.500 -0.1117 0.02066 0.01227 -0.0684 0.7211 0.0237
-4.250 -0.0908 0.01997 0.01154 -0.0674 0.7188 0.0269
-4.000 -0.0685 0.01957 0.01109 -0.0667 0.7170 0.0298
-3.750 -0.0449 0.01934 0.01077 -0.0661 0.7155 0.0347
-3.500 -0.0231 0.01888 0.01030 -0.0652 0.7142 0.0415
-3.250 0.0001 0.01855 0.00990 -0.0644 0.7130 0.0502
-3.000 0.0238 0.01823 0.00952 -0.0637 0.7120 0.0617
-2.750 0.0474 0.01792 0.00917 -0.0630 0.7110 0.0751
-2.500 0.0707 0.01759 0.00889 -0.0624 0.7102 0.0972
-2.250 0.0873 0.01777 0.00929 -0.0612 0.7061 0.1354
-2.000 0.1052 0.01750 0.00931 -0.0599 0.7034 0.2128
-1.750 0.1219 0.01706 0.00923 -0.0582 0.7016 0.3263
-1.500 0.1308 0.01627 0.00915 -0.0548 0.7000 0.5167
-1.250 0.1628 0.01543 0.00935 -0.0550 0.6992 0.8148
-1.000 0.2215 0.01548 0.00937 -0.0611 0.6987 0.8850
-0.750 0.2786 0.01564 0.00943 -0.0669 0.6982 0.9196
-0.500 0.3459 0.01601 0.00968 -0.0743 0.6979 0.9474
-0.250 0.3989 0.01618 0.00973 -0.0794 0.6974 0.9599
0.000 0.4317 0.01622 0.00967 -0.0806 0.6966 0.9671
0.250 0.4645 0.01689 0.01037 -0.0831 0.6916 0.9712
0.500 0.4959 0.01707 0.01051 -0.0845 0.6894 0.9753
0.750 0.5249 0.01716 0.01056 -0.0853 0.6877 0.9798
1.000 0.5592 0.01712 0.01047 -0.0870 0.6864 0.9824
1.250 0.5921 0.01710 0.01042 -0.0885 0.6853 0.9855
1.500 0.6232 0.01707 0.01036 -0.0895 0.6843 0.9888
1.750 0.6566 0.01696 0.01022 -0.0910 0.6835 0.9912
2.250 0.7167 0.01782 0.01119 -0.0943 0.6751 0.9986
2.500 0.7457 0.01776 0.01113 -0.0949 0.6733 1.0000
2.750 0.7674 0.01769 0.01106 -0.0940 0.6718 1.0000
3.000 0.7905 0.01753 0.01090 -0.0932 0.6706 1.0000
3.500 0.8146 0.01854 0.01206 -0.0891 0.6610 1.0000
3.750 0.8360 0.01846 0.01200 -0.0880 0.6591 1.0000
4.000 0.8599 0.01824 0.01181 -0.0873 0.6577 1.0000
4.250 0.8852 0.01798 0.01157 -0.0867 0.6565 1.0000
4.750 0.9024 0.01911 0.01287 -0.0813 0.6455 1.0000
5.000 0.9279 0.01886 0.01267 -0.0808 0.6440 1.0000
5.250 0.9547 0.01854 0.01240 -0.0804 0.6424 1.0000
5.750 0.9705 0.01957 0.01360 -0.0746 0.6307 1.0000
6.000 0.9999 0.01918 0.01331 -0.0746 0.6294 1.0000
6.500 0.9985 0.02080 0.01507 -0.0665 0.6144 1.0000
7.500 1.0266 0.02260 0.01711 -0.0550 0.5711 1.0000
7.750 1.0652 0.02064 0.01509 -0.0549 0.5315 1.0000
8.000 1.0793 0.02005 0.01373 -0.0513 0.4299 1.0000
8.250 1.0519 0.02264 0.01574 -0.0448 0.3515 1.0000
8.500 1.0282 0.02545 0.01803 -0.0396 0.2772 1.0000
8.750 1.0190 0.02762 0.01989 -0.0363 0.2246 1.0000
9.000 1.0019 0.03044 0.02221 -0.0324 0.1497 1.0000
9.250 0.9828 0.03363 0.02479 -0.0286 0.0624 1.0000
9.500 0.9769 0.03610 0.02696 -0.0260 0.0222 1.0000
9.750 0.9859 0.03746 0.02837 -0.0248 0.0181 1.0000
10.000 0.9923 0.03912 0.03008 -0.0233 0.0145 1.0000
10.250 1.0007 0.04064 0.03172 -0.0220 0.0124 1.0000
10.500 1.0080 0.04228 0.03348 -0.0207 0.0112 1.0000
10.750 1.0120 0.04422 0.03552 -0.0194 0.0099 1.0000
11.000 1.0132 0.04652 0.03793 -0.0178 0.0092 1.0000
11.250 1.0214 0.04818 0.03974 -0.0168 0.0085 1.0000
11.500 1.0239 0.05039 0.04205 -0.0155 0.0089 1.0000
11.750 1.0360 0.05171 0.04345 -0.0150 0.0076 1.0000
12.000 1.0399 0.05384 0.04566 -0.0139 0.0067 1.0000
12.250 1.0472 0.05566 0.04756 -0.0129 0.0067 1.0000
12.500 1.0543 0.05749 0.04950 -0.0118 0.0071 1.0000
12.750 1.0599 0.05948 0.05155 -0.0107 0.0064 1.0000
13.000 1.0676 0.06128 0.05342 -0.0096 0.0061 1.0000
13.250 1.0771 0.06291 0.05513 -0.0086 0.0060 1.0000
13.500 1.0875 0.06451 0.05684 -0.0077 0.0060 1.0000
13.750 1.1019 0.06600 0.05844 -0.0053 0.0056 1.0000
14.000 1.1127 0.06792 0.06053 -0.0042 0.0056 1.0000
14.250 1.1180 0.07027 0.06313 -0.0036 0.0055 1.0000
14.750 1.1257 0.07581 0.06909 -0.0021 0.0055 1.0000
15.000 1.1223 0.07966 0.07325 -0.0013 0.0054 1.0000
15.250 1.1186 0.08326 0.07707 -0.0012 0.0054 1.0000
15.500 1.1096 0.08797 0.08206 -0.0010 0.0054 1.0000
15.750 1.1073 0.09147 0.08568 -0.0012 0.0055 1.0000
16.000 1.0921 0.09723 0.09173 -0.0018 0.0055 1.0000
16.250 1.0820 0.10214 0.09684 -0.0029 0.0055 1.0000
16.500 1.0712 0.10736 0.10225 -0.0042 0.0055 1.0000
16.750 1.0577 0.11331 0.10840 -0.0061 0.0055 1.0000
17.000 1.0426 0.11981 0.11510 -0.0086 0.0055 1.0000
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