FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 78-K-140 A/20 (fx78k140a20-il) Reynolds number: 200,000 Max Cl/Cd: 57.45 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx78k140a20-il-200000-n5.txt Download as CSV file: xf-fx78k140a20-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1333 0.09290 0.08813 -0.1014 0.7506 0.0148
-10.250 -0.1325 0.08920 0.08448 -0.1030 0.7494 0.0145
-10.000 -0.1455 0.08216 0.07754 -0.1059 0.7482 0.0129
-9.750 -0.1425 0.07905 0.07443 -0.1071 0.7467 0.0112
-9.500 -0.1425 0.07631 0.07176 -0.1085 0.7452 0.0139
-9.250 -0.1538 0.07056 0.06608 -0.1116 0.7438 0.0133
-9.000 -0.1745 0.06320 0.05882 -0.1167 0.7424 0.0129
-8.750 -0.1804 0.06039 0.05595 -0.1168 0.7412 0.0102
-8.500 -0.2075 0.05365 0.04913 -0.1162 0.7399 0.0119
-8.250 -0.2243 0.04929 0.04460 -0.1139 0.7387 0.0119
-8.000 -0.2382 0.04472 0.03976 -0.1111 0.7377 0.0120
-7.750 -0.2434 0.04161 0.03645 -0.1084 0.7359 0.0119
-7.500 -0.2520 0.03733 0.03175 -0.1048 0.7338 0.0122
-7.000 -0.2455 0.03131 0.02498 -0.0994 0.7307 0.0129
-6.750 -0.2324 0.02929 0.02263 -0.0975 0.7294 0.0132
-6.500 -0.2156 0.02771 0.02071 -0.0961 0.7282 0.0137
-6.250 -0.1963 0.02642 0.01916 -0.0950 0.7270 0.0146
-6.000 -0.1744 0.02574 0.01825 -0.0942 0.7260 0.0167
-5.750 -0.1525 0.02422 0.01640 -0.0932 0.7250 0.0178
-5.500 -0.1291 0.02294 0.01484 -0.0924 0.7243 0.0185
-5.250 -0.1075 0.02175 0.01349 -0.0915 0.7229 0.0193
-5.000 -0.0874 0.02088 0.01258 -0.0904 0.7208 0.0212
-4.750 -0.0655 0.02036 0.01200 -0.0896 0.7189 0.0231
-4.500 -0.0428 0.01995 0.01147 -0.0889 0.7172 0.0265
-4.250 -0.0207 0.01945 0.01094 -0.0881 0.7157 0.0315
-4.000 0.0022 0.01908 0.01051 -0.0873 0.7145 0.0363
-3.750 0.0253 0.01873 0.01013 -0.0867 0.7134 0.0440
-3.500 0.0492 0.01842 0.00973 -0.0861 0.7124 0.0524
-3.250 0.0730 0.01810 0.00939 -0.0855 0.7115 0.0653
-3.000 0.0972 0.01779 0.00905 -0.0850 0.7106 0.0808
-2.750 0.1170 0.01772 0.00909 -0.0840 0.7082 0.1004
-2.500 0.1362 0.01758 0.00915 -0.0829 0.7057 0.1447
-2.250 0.1546 0.01718 0.00911 -0.0817 0.7035 0.2374
-2.000 0.1712 0.01663 0.00902 -0.0801 0.7018 0.3698
-1.750 0.1823 0.01582 0.00892 -0.0771 0.7003 0.5642
-1.500 0.1999 0.01582 0.00976 -0.0732 0.6992 0.8063
-1.250 0.2183 0.01595 0.00975 -0.0713 0.6981 0.8450
-1.000 0.2384 0.01612 0.00983 -0.0692 0.6972 0.8716
-0.750 0.2558 0.01659 0.01030 -0.0668 0.6944 0.8923
-0.500 0.2705 0.01705 0.01076 -0.0639 0.6911 0.9146
-0.250 0.3145 0.01731 0.01097 -0.0664 0.6896 0.9370
0.000 0.3658 0.01744 0.01100 -0.0712 0.6884 0.9469
0.250 0.3969 0.01746 0.01094 -0.0722 0.6871 0.9506
0.500 0.4183 0.01743 0.01085 -0.0712 0.6857 0.9543
0.750 0.4482 0.01739 0.01075 -0.0719 0.6847 0.9559
1.000 0.4805 0.01732 0.01061 -0.0731 0.6838 0.9571
1.250 0.5123 0.01725 0.01048 -0.0742 0.6830 0.9582
1.500 0.5272 0.01803 0.01135 -0.0732 0.6765 0.9616
1.750 0.5531 0.01805 0.01135 -0.0732 0.6743 0.9637
2.000 0.5788 0.01801 0.01131 -0.0731 0.6728 0.9658
2.250 0.6035 0.01790 0.01117 -0.0727 0.6715 0.9682
2.500 0.6357 0.01777 0.01102 -0.0738 0.6705 0.9691
2.750 0.6679 0.01764 0.01088 -0.0750 0.6696 0.9698
3.250 0.7100 0.01851 0.01191 -0.0744 0.6600 0.9741
3.500 0.7389 0.01839 0.01181 -0.0749 0.6585 0.9752
3.750 0.7678 0.01821 0.01165 -0.0753 0.6573 0.9762
4.000 0.7978 0.01799 0.01148 -0.0758 0.6562 0.9771
4.500 0.8372 0.01884 0.01251 -0.0747 0.6459 0.9821
4.750 0.8682 0.01864 0.01237 -0.0755 0.6444 0.9830
5.000 0.8999 0.01838 0.01219 -0.0763 0.6432 0.9837
5.500 0.9399 0.01920 0.01325 -0.0754 0.6324 0.9895
5.750 0.9717 0.01892 0.01306 -0.0763 0.6307 0.9904
6.000 0.9981 0.01903 0.01329 -0.0767 0.6266 0.9925
6.250 1.0001 0.01965 0.01402 -0.0730 0.6191 1.0000
6.500 1.0226 0.01937 0.01386 -0.0719 0.6169 1.0000
6.750 1.0512 0.01895 0.01355 -0.0719 0.6152 1.0000
7.000 1.0212 0.02032 0.01496 -0.0632 0.6035 1.0000
7.500 1.0303 0.02200 0.01681 -0.0583 0.5809 1.0000
7.750 1.0807 0.01881 0.01344 -0.0587 0.5299 1.0000
8.000 1.0841 0.01896 0.01276 -0.0543 0.4231 1.0000
8.250 1.0642 0.02154 0.01484 -0.0497 0.3531 1.0000
8.500 1.0547 0.02378 0.01683 -0.0465 0.3005 1.0000
8.750 1.0324 0.02698 0.01944 -0.0424 0.2198 1.0000
9.000 1.0177 0.02985 0.02187 -0.0392 0.1471 1.0000
9.250 1.0036 0.03280 0.02431 -0.0362 0.0718 1.0000
9.500 0.9945 0.03553 0.02668 -0.0337 0.0235 1.0000
9.750 1.0038 0.03699 0.02820 -0.0327 0.0190 1.0000
10.000 1.0087 0.03889 0.03015 -0.0313 0.0137 1.0000
10.250 1.0188 0.04039 0.03175 -0.0305 0.0122 1.0000
10.500 1.0277 0.04202 0.03350 -0.0296 0.0114 1.0000
10.750 1.0356 0.04378 0.03539 -0.0287 0.0106 1.0000
11.000 1.0418 0.04572 0.03743 -0.0277 0.0097 1.0000
11.250 1.0476 0.04771 0.03953 -0.0268 0.0093 1.0000
11.500 1.0507 0.04997 0.04188 -0.0258 0.0088 1.0000
11.750 1.0528 0.05235 0.04435 -0.0246 0.0084 1.0000
12.250 1.0618 0.05659 0.04879 -0.0221 0.0079 1.0000
12.500 1.0724 0.05819 0.05050 -0.0214 0.0076 1.0000
12.750 1.0823 0.05978 0.05218 -0.0202 0.0075 1.0000
13.000 1.0918 0.06171 0.05423 -0.0204 0.0058 1.0000
13.250 1.1023 0.06330 0.05593 -0.0193 0.0060 1.0000
13.500 1.1108 0.06518 0.05792 -0.0184 0.0056 1.0000
13.750 1.1196 0.06707 0.05991 -0.0177 0.0054 1.0000
14.000 1.1273 0.06912 0.06207 -0.0170 0.0052 1.0000
14.250 1.1362 0.07118 0.06431 -0.0161 0.0052 1.0000
14.500 1.1406 0.07387 0.06713 -0.0149 0.0049 1.0000
14.750 1.1461 0.07635 0.06983 -0.0147 0.0051 1.0000
15.000 1.1410 0.08056 0.07430 -0.0135 0.0047 1.0000
15.250 1.1442 0.08334 0.07725 -0.0136 0.0049 1.0000
15.500 1.1353 0.08811 0.08231 -0.0133 0.0048 1.0000
15.750 1.1249 0.09302 0.08752 -0.0140 0.0047 1.0000
16.000 1.1173 0.09759 0.09228 -0.0146 0.0048 1.0000
16.500 1.0967 0.10805 0.10316 -0.0174 0.0048 1.0000
16.750 1.0811 0.11462 0.10998 -0.0199 0.0048 1.0000
17.250 1.0679 0.12508 0.12080 -0.0247 0.0050 1.0000
17.500 1.0483 0.13316 0.12907 -0.0286 0.0049 1.0000
17.750 1.0313 0.14136 0.13746 -0.0331 0.0049 1.0000
18.000 1.0180 0.14940 0.14568 -0.0380 0.0049 1.0000
18.250 1.0066 0.15818 0.15471 -0.0436 0.0052 1.0000
18.500 0.9899 0.16815 0.16477 -0.0498 0.0050 1.0000
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