FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 78-K-140 A/20 (fx78k140a20-il) Reynolds number: 100,000 Max Cl/Cd: 27.77 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx78k140a20-il-100000-n5.txt Download as CSV file: xf-fx78k140a20-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1376 0.10985 0.10401 -0.0997 0.7968 0.0418
-11.000 -0.0730 0.09019 0.08485 -0.0951 0.7887 0.0274
-10.750 -0.1317 0.10121 0.09536 -0.1030 0.7945 0.0270
-10.500 -0.1300 0.09729 0.09148 -0.1041 0.7934 0.0265
-10.250 -0.1264 0.09415 0.08835 -0.1051 0.7922 0.0256
-10.000 -0.1263 0.09053 0.08477 -0.1065 0.7910 0.0254
-9.750 -0.1242 0.08755 0.08182 -0.1075 0.7895 0.0245
-9.500 -0.1291 0.08328 0.07765 -0.1092 0.7878 0.0248
-9.250 -0.1313 0.07974 0.07416 -0.1106 0.7861 0.0238
-9.000 -0.1368 0.07571 0.07021 -0.1127 0.7846 0.0238
-8.750 -0.1435 0.07168 0.06624 -0.1152 0.7829 0.0233
-8.500 -0.1572 0.06720 0.06178 -0.1171 0.7810 0.0229
-8.250 -0.1743 0.06375 0.05829 -0.1165 0.7791 0.0226
-8.000 -0.1880 0.06049 0.05496 -0.1152 0.7772 0.0224
-7.750 -0.1967 0.05736 0.05174 -0.1138 0.7750 0.0221
-7.500 -0.2012 0.05468 0.04893 -0.1122 0.7730 0.0236
-7.250 -0.2047 0.05150 0.04553 -0.1102 0.7711 0.0229
-7.000 -0.2053 0.04858 0.04230 -0.1080 0.7691 0.0254
-6.750 -0.2029 0.04558 0.03896 -0.1056 0.7672 0.0256
-6.500 -0.1969 0.04275 0.03573 -0.1032 0.7656 0.0257
-6.250 -0.1895 0.04006 0.03259 -0.1008 0.7638 0.0261
-6.000 -0.1803 0.03777 0.02987 -0.0984 0.7615 0.0264
-5.750 -0.1675 0.03570 0.02735 -0.0962 0.7591 0.0272
-5.500 -0.1505 0.03396 0.02515 -0.0944 0.7569 0.0280
-5.250 -0.1317 0.03215 0.02307 -0.0932 0.7550 0.0292
-5.000 -0.1116 0.03154 0.02238 -0.0924 0.7535 0.0331
-4.750 -0.0886 0.03058 0.02115 -0.0916 0.7522 0.0368
-4.500 -0.0639 0.02954 0.01977 -0.0908 0.7511 0.0397
-4.250 -0.0516 0.02909 0.01942 -0.0891 0.7475 0.0448
-4.000 -0.0335 0.02871 0.01892 -0.0876 0.7447 0.0509
-3.750 -0.0155 0.02811 0.01828 -0.0862 0.7426 0.0563
-3.500 0.0048 0.02777 0.01786 -0.0851 0.7407 0.0669
-3.250 0.0256 0.02734 0.01737 -0.0840 0.7391 0.0797
-3.000 0.0479 0.02689 0.01695 -0.0831 0.7377 0.0979
-2.750 0.0545 0.02715 0.01728 -0.0804 0.7333 0.1159
-2.500 0.0689 0.02700 0.01732 -0.0786 0.7302 0.1587
-2.250 0.0858 0.02646 0.01726 -0.0771 0.7278 0.2726
-2.000 0.0948 0.02541 0.01723 -0.0740 0.7259 0.5196
-1.500 0.1057 0.02650 0.01916 -0.0634 0.7193 0.8724
-1.250 0.1288 0.02704 0.01955 -0.0618 0.7162 0.9117
-1.000 0.3667 0.02670 0.01849 -0.0995 0.7247 0.9772
-0.750 0.4101 0.02692 0.01857 -0.1036 0.7225 0.9860
-0.500 0.4355 0.02753 0.01912 -0.1049 0.7183 0.9921
-0.250 0.4652 0.02781 0.01929 -0.1063 0.7157 0.9965
0.000 0.4956 0.02797 0.01937 -0.1076 0.7136 0.9999
0.250 0.5147 0.02813 0.01945 -0.1065 0.7117 1.0000
0.750 0.5189 0.02961 0.02090 -0.0994 0.7018 1.0000
1.000 0.5352 0.02982 0.02106 -0.0977 0.6993 1.0000
1.250 0.5560 0.02991 0.02109 -0.0966 0.6975 1.0000
1.750 0.5497 0.03142 0.02260 -0.0878 0.6860 1.0000
2.000 0.5715 0.03144 0.02261 -0.0868 0.6841 1.0000
2.500 0.5562 0.03282 0.02397 -0.0762 0.6719 1.0000
2.750 0.5798 0.03282 0.02396 -0.0755 0.6702 1.0000
3.250 0.5623 0.03388 0.02500 -0.0644 0.6573 1.0000
3.750 0.5653 0.03498 0.02608 -0.0572 0.6451 1.0000
4.000 0.5922 0.03494 0.02607 -0.0570 0.6433 1.0000
4.500 0.6094 0.03613 0.02728 -0.0525 0.6310 1.0000
4.750 0.6381 0.03606 0.02724 -0.0526 0.6293 1.0000
5.000 0.6348 0.03731 0.02852 -0.0495 0.6193 1.0000
5.250 0.6630 0.03723 0.02849 -0.0495 0.6168 1.0000
5.750 0.6921 0.03841 0.02981 -0.0471 0.6046 1.0000
6.000 0.7207 0.03832 0.02980 -0.0472 0.6024 1.0000
6.250 0.7242 0.03956 0.03109 -0.0452 0.5925 1.0000
6.500 0.7521 0.03946 0.03110 -0.0452 0.5897 1.0000
7.000 0.7863 0.04048 0.03235 -0.0436 0.5770 1.0000
7.250 0.8165 0.04022 0.03223 -0.0437 0.5748 1.0000
7.500 0.8210 0.04160 0.03370 -0.0421 0.5643 1.0000
7.750 0.8515 0.04119 0.03345 -0.0422 0.5616 1.0000
8.000 0.8587 0.04244 0.03487 -0.0408 0.5513 1.0000
8.250 0.8881 0.04206 0.03467 -0.0407 0.5483 1.0000
8.750 0.9290 0.04235 0.03532 -0.0393 0.5344 1.0000
9.500 0.9969 0.03863 0.03201 -0.0344 0.4603 1.0000
9.750 1.0165 0.03660 0.02877 -0.0304 0.3035 1.0000
10.000 0.9973 0.03975 0.03115 -0.0269 0.2030 1.0000
10.250 0.9855 0.04280 0.03360 -0.0245 0.1214 1.0000
10.500 0.9738 0.04596 0.03608 -0.0220 0.0469 1.0000
10.750 0.9744 0.04828 0.03826 -0.0205 0.0308 1.0000
11.000 0.9797 0.05029 0.04036 -0.0192 0.0254 1.0000
11.250 0.9846 0.05236 0.04256 -0.0181 0.0230 1.0000
11.500 0.9867 0.05473 0.04505 -0.0170 0.0212 1.0000
11.750 0.9893 0.05712 0.04759 -0.0159 0.0199 1.0000
12.000 0.9960 0.05912 0.04975 -0.0151 0.0176 1.0000
12.250 1.0018 0.06122 0.05195 -0.0143 0.0159 1.0000
12.500 1.0082 0.06326 0.05411 -0.0134 0.0157 1.0000
12.750 1.0136 0.06537 0.05634 -0.0126 0.0144 1.0000
13.000 1.0228 0.06708 0.05811 -0.0110 0.0137 1.0000
13.250 1.0383 0.06828 0.05938 -0.0096 0.0133 1.0000
13.500 1.0581 0.06952 0.06077 -0.0081 0.0128 1.0000
13.750 1.0748 0.07121 0.06267 -0.0071 0.0126 1.0000
14.000 1.0888 0.07340 0.06510 -0.0062 0.0125 1.0000
14.250 1.0980 0.07607 0.06803 -0.0054 0.0123 1.0000
14.500 1.1011 0.07943 0.07171 -0.0048 0.0121 1.0000
14.750 1.1021 0.08283 0.07536 -0.0045 0.0122 1.0000
15.000 1.0942 0.08702 0.07988 -0.0044 0.0113 1.0000
15.250 1.0900 0.09130 0.08439 -0.0045 0.0120 1.0000
15.500 1.0793 0.09590 0.08929 -0.0052 0.0115 1.0000
15.750 1.0669 0.10104 0.09469 -0.0063 0.0110 1.0000
16.000 1.0549 0.10644 0.10035 -0.0077 0.0112 1.0000
16.250 1.0416 0.11237 0.10648 -0.0096 0.0117 1.0000
16.500 1.0271 0.11852 0.11287 -0.0124 0.0112 1.0000
16.750 1.0104 0.12559 0.12016 -0.0157 0.0111 1.0000
17.000 0.9973 0.13234 0.12706 -0.0191 0.0119 1.0000
17.250 0.9827 0.13980 0.13465 -0.0230 0.0125 1.0000
17.500 0.9650 0.14878 0.14381 -0.0287 0.0122 1.0000
17.750 0.9481 0.15848 0.15365 -0.0348 0.0123 1.0000
18.000 0.9334 0.16865 0.16390 -0.0411 0.0124 1.0000
18.250 0.9317 0.17403 0.16926 -0.0439 0.0131 1.0000
18.500 0.9184 0.18638 0.18165 -0.0511 0.0129 1.0000
18.750 0.6626 0.16935 0.16533 -0.0390 0.0158 1.0000
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