FX 78-K-150/20 (fx78k150-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 78-K-150/20 (fx78k150-il) Reynolds number: 200,000 Max Cl/Cd: 49.98 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx78k150-il-200000-n5.txt Download as CSV file: xf-fx78k150-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-150/20
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1903 0.10058 0.09573 -0.0975 0.7454 0.0159
-11.750 -0.1938 0.09566 0.09081 -0.0995 0.7445 0.0159
-11.500 -0.2022 0.08978 0.08497 -0.1019 0.7437 0.0160
-11.250 -0.2037 0.08581 0.08102 -0.1037 0.7429 0.0159
-11.000 -0.2177 0.07931 0.07456 -0.1066 0.7420 0.0159
-10.750 -0.2161 0.07645 0.07172 -0.1080 0.7409 0.0155
-10.500 -0.2850 0.05702 0.05244 -0.1199 0.7397 0.0155
-10.250 -0.3167 0.05079 0.04611 -0.1223 0.7381 0.0152
-10.000 -0.3355 0.04752 0.04273 -0.1212 0.7365 0.0149
-9.750 -0.3684 0.04354 0.03854 -0.1173 0.7348 0.0149
-9.500 -0.3912 0.04058 0.03532 -0.1126 0.7333 0.0150
-9.250 -0.4073 0.03709 0.03142 -0.1085 0.7318 0.0150
-9.000 -0.4132 0.03400 0.02785 -0.1050 0.7306 0.0155
-8.750 -0.4100 0.03148 0.02490 -0.1022 0.7293 0.0157
-8.500 -0.4005 0.02942 0.02244 -0.1001 0.7283 0.0161
-8.250 -0.3871 0.02792 0.02074 -0.0985 0.7274 0.0168
-8.000 -0.3703 0.02702 0.01971 -0.0973 0.7261 0.0175
-7.750 -0.3527 0.02609 0.01863 -0.0962 0.7246 0.0183
-7.500 -0.3333 0.02536 0.01772 -0.0952 0.7231 0.0199
-7.250 -0.3129 0.02447 0.01656 -0.0942 0.7216 0.0216
-7.000 -0.2932 0.02351 0.01552 -0.0933 0.7201 0.0231
-6.750 -0.2717 0.02294 0.01487 -0.0926 0.7186 0.0248
-6.500 -0.2493 0.02234 0.01414 -0.0920 0.7173 0.0273
-6.250 -0.2265 0.02174 0.01338 -0.0913 0.7162 0.0302
-6.000 -0.2041 0.02123 0.01282 -0.0907 0.7153 0.0331
-5.750 -0.1809 0.02075 0.01225 -0.0902 0.7144 0.0361
-5.500 -0.1570 0.02035 0.01170 -0.0897 0.7136 0.0398
-5.250 -0.1345 0.01983 0.01117 -0.0890 0.7128 0.0438
-5.000 -0.1130 0.01965 0.01096 -0.0883 0.7108 0.0482
-4.750 -0.0919 0.01941 0.01067 -0.0874 0.7086 0.0526
-4.500 -0.0704 0.01912 0.01039 -0.0866 0.7068 0.0576
-4.250 -0.0476 0.01894 0.01014 -0.0860 0.7053 0.0632
-4.000 -0.0255 0.01867 0.00988 -0.0853 0.7040 0.0706
-3.750 -0.0022 0.01847 0.00963 -0.0847 0.7028 0.0788
-3.500 0.0210 0.01821 0.00936 -0.0841 0.7016 0.0900
-3.250 0.0446 0.01795 0.00912 -0.0836 0.7006 0.1061
-3.000 0.0680 0.01765 0.00890 -0.0830 0.6997 0.1310
-2.750 0.0908 0.01732 0.00869 -0.0824 0.6989 0.1746
-2.500 0.1089 0.01717 0.00880 -0.0812 0.6969 0.2363
-2.250 0.1242 0.01712 0.00905 -0.0796 0.6941 0.3100
-2.000 0.1381 0.01675 0.00912 -0.0775 0.6918 0.4215
-1.750 0.1460 0.01606 0.00920 -0.0737 0.6899 0.6089
-1.500 0.1665 0.01614 0.00986 -0.0711 0.6886 0.7778
-1.250 0.1867 0.01636 0.01001 -0.0694 0.6874 0.8194
-1.000 0.2070 0.01650 0.01006 -0.0679 0.6864 0.8424
-0.750 0.2307 0.01664 0.01013 -0.0667 0.6856 0.8597
-0.500 0.2550 0.01677 0.01023 -0.0655 0.6848 0.8793
-0.250 0.2642 0.01748 0.01100 -0.0622 0.6802 0.8966
0.000 0.2802 0.01784 0.01137 -0.0599 0.6774 0.9152
0.250 0.3135 0.01803 0.01153 -0.0608 0.6760 0.9311
0.500 0.3507 0.01811 0.01156 -0.0628 0.6747 0.9380
0.750 0.3736 0.01811 0.01151 -0.0621 0.6735 0.9434
1.000 0.4061 0.01810 0.01144 -0.0634 0.6725 0.9452
1.250 0.4383 0.01809 0.01139 -0.0647 0.6717 0.9469
1.500 0.4700 0.01806 0.01131 -0.0658 0.6710 0.9487
2.000 0.4987 0.01935 0.01269 -0.0632 0.6618 0.9580
2.250 0.5296 0.01942 0.01276 -0.0643 0.6604 0.9593
2.500 0.5618 0.01940 0.01272 -0.0656 0.6593 0.9607
2.750 0.5943 0.01934 0.01267 -0.0668 0.6584 0.9622
3.000 0.6265 0.01927 0.01259 -0.0679 0.6576 0.9636
3.250 0.6584 0.01917 0.01251 -0.0690 0.6568 0.9650
4.250 0.7616 0.02066 0.01425 -0.0715 0.6442 0.9755
4.500 0.7955 0.02050 0.01415 -0.0729 0.6434 0.9769
4.750 0.8284 0.02037 0.01407 -0.0741 0.6422 0.9787
5.250 0.8273 0.02391 0.01783 -0.0699 0.6232 1.0000
6.250 0.9047 0.02401 0.01819 -0.0654 0.6140 1.0000
6.750 0.8990 0.02742 0.02172 -0.0600 0.5938 1.0000
7.000 0.9521 0.02430 0.01870 -0.0614 0.5890 1.0000
7.250 0.9581 0.02546 0.01993 -0.0596 0.5776 1.0000
7.500 0.9913 0.02361 0.01804 -0.0592 0.5407 1.0000
7.750 1.0336 0.02068 0.01425 -0.0578 0.4213 1.0000
8.000 1.0120 0.02346 0.01652 -0.0530 0.3476 1.0000
8.250 0.9931 0.02638 0.01900 -0.0491 0.2779 1.0000
8.500 0.9575 0.03058 0.02241 -0.0440 0.1596 1.0000
8.750 0.9356 0.03407 0.02525 -0.0403 0.0610 1.0000
9.000 0.9362 0.03618 0.02718 -0.0386 0.0320 1.0000
9.250 0.9448 0.03773 0.02874 -0.0375 0.0247 1.0000
9.500 0.9549 0.03921 0.03030 -0.0366 0.0214 1.0000
9.750 0.9647 0.04073 0.03189 -0.0357 0.0189 1.0000
10.000 0.9742 0.04230 0.03354 -0.0348 0.0179 1.0000
10.250 0.9829 0.04396 0.03527 -0.0339 0.0174 1.0000
10.500 0.9881 0.04596 0.03736 -0.0328 0.0163 1.0000
10.750 0.9951 0.04783 0.03933 -0.0318 0.0156 1.0000
11.000 1.0036 0.04956 0.04117 -0.0310 0.0155 1.0000
11.250 1.0122 0.05128 0.04297 -0.0301 0.0149 1.0000
11.500 1.0238 0.05276 0.04448 -0.0297 0.0129 1.0000
11.750 1.0316 0.05457 0.04635 -0.0288 0.0128 1.0000
12.000 1.0398 0.05634 0.04817 -0.0279 0.0124 1.0000
12.250 1.0456 0.05815 0.04997 -0.0265 0.0116 1.0000
12.500 1.0578 0.05946 0.05135 -0.0256 0.0117 1.0000
12.750 1.0712 0.06070 0.05268 -0.0247 0.0113 1.0000
13.000 1.0865 0.06172 0.05380 -0.0235 0.0113 1.0000
13.250 1.1022 0.06282 0.05501 -0.0225 0.0111 1.0000
13.500 1.1191 0.06388 0.05620 -0.0214 0.0109 1.0000
13.750 1.1344 0.06522 0.05772 -0.0203 0.0105 1.0000
14.000 1.1493 0.06674 0.05941 -0.0193 0.0105 1.0000
14.250 1.1605 0.06877 0.06167 -0.0184 0.0101 1.0000
14.500 1.1698 0.07116 0.06430 -0.0173 0.0100 1.0000
14.750 1.1736 0.07374 0.06705 -0.0168 0.0095 1.0000
15.000 1.1773 0.07701 0.07063 -0.0157 0.0099 1.0000
15.250 1.1756 0.08026 0.07411 -0.0153 0.0095 1.0000
15.500 1.1767 0.08273 0.07662 -0.0157 0.0088 1.0000
15.750 1.1734 0.08638 0.08049 -0.0155 0.0088 1.0000
16.000 1.1711 0.08945 0.08358 -0.0161 0.0083 1.0000
16.250 1.1663 0.09333 0.08764 -0.0164 0.0082 1.0000
16.500 1.1515 0.09919 0.09390 -0.0166 0.0085 1.0000
16.750 1.1405 0.10430 0.09923 -0.0175 0.0085 1.0000
17.000 1.1305 0.10929 0.10438 -0.0189 0.0084 1.0000
17.250 1.1173 0.11509 0.11039 -0.0208 0.0083 1.0000
17.500 1.1007 0.12172 0.11720 -0.0232 0.0082 1.0000
17.750 1.0846 0.12853 0.12419 -0.0262 0.0081 1.0000
18.000 1.0708 0.13552 0.13140 -0.0298 0.0082 1.0000
18.250 1.0524 0.14374 0.13980 -0.0342 0.0081 1.0000
18.500 1.0057 0.16168 0.15819 -0.0446 0.0087 1.0000
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