FX 78-K-150/20 (fx78k150-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 78-K-150/20 (fx78k150-il) Reynolds number: 100,000 Max Cl/Cd: 23.53 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx78k150-il-100000-n5.txt Download as CSV file: xf-fx78k150-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.1795 0.13562 0.12961 -0.0874 0.7940 0.0470
-13.250 -0.1732 0.13238 0.12639 -0.0890 0.7928 0.0460
-12.750 -0.1839 0.12063 0.11468 -0.0952 0.7908 0.0294
-12.500 -0.1753 0.11758 0.11162 -0.0959 0.7897 0.0288
-12.250 -0.1718 0.11380 0.10786 -0.0972 0.7886 0.0286
-12.000 -0.1673 0.11046 0.10452 -0.0984 0.7875 0.0281
-11.750 -0.1665 0.10649 0.10055 -0.1000 0.7863 0.0281
-11.500 -0.1682 0.10211 0.09620 -0.1019 0.7852 0.0284
-11.250 -0.1662 0.09875 0.09285 -0.1033 0.7841 0.0282
-11.000 -0.1694 0.09436 0.08851 -0.1052 0.7827 0.0284
-10.750 -0.1661 0.09148 0.08566 -0.1061 0.7811 0.0274
-10.500 -0.1856 0.08370 0.07801 -0.1105 0.7798 0.0293
-10.250 -0.1923 0.07895 0.07332 -0.1127 0.7783 0.0292
-10.000 -0.1940 0.07566 0.07007 -0.1140 0.7769 0.0285
-9.750 -0.2113 0.06854 0.06300 -0.1189 0.7753 0.0284
-9.500 -0.2296 0.06349 0.05791 -0.1212 0.7736 0.0282
-9.250 -0.2492 0.05959 0.05393 -0.1210 0.7718 0.0276
-9.000 -0.2761 0.05630 0.05047 -0.1184 0.7701 0.0282
-8.750 -0.2925 0.05358 0.04764 -0.1158 0.7676 0.0280
-8.500 -0.3075 0.05042 0.04421 -0.1129 0.7654 0.0282
-8.250 -0.3192 0.04715 0.04054 -0.1098 0.7634 0.0288
-8.000 -0.3237 0.04419 0.03713 -0.1068 0.7615 0.0292
-7.750 -0.3225 0.04146 0.03396 -0.1041 0.7598 0.0297
-7.500 -0.3136 0.03947 0.03174 -0.1022 0.7582 0.0306
-7.250 -0.3004 0.03809 0.03013 -0.1007 0.7567 0.0320
-7.000 -0.2868 0.03694 0.02875 -0.0991 0.7549 0.0338
-6.750 -0.2736 0.03583 0.02734 -0.0975 0.7526 0.0365
-6.500 -0.2586 0.03447 0.02550 -0.0958 0.7505 0.0391
-6.250 -0.2416 0.03307 0.02397 -0.0947 0.7484 0.0412
-6.000 -0.2230 0.03257 0.02335 -0.0937 0.7465 0.0450
-5.750 -0.2017 0.03170 0.02219 -0.0927 0.7448 0.0492
-5.500 -0.1798 0.03063 0.02097 -0.0920 0.7434 0.0530
-5.250 -0.1579 0.03011 0.02038 -0.0913 0.7423 0.0583
-5.000 -0.1377 0.02968 0.01974 -0.0902 0.7406 0.0634
-4.750 -0.1258 0.02944 0.01956 -0.0884 0.7372 0.0671
-4.500 -0.1096 0.02930 0.01937 -0.0870 0.7343 0.0741
-4.250 -0.0916 0.02895 0.01895 -0.0857 0.7322 0.0803
-4.000 -0.0727 0.02867 0.01863 -0.0844 0.7305 0.0875
-3.750 -0.0526 0.02838 0.01833 -0.0834 0.7291 0.0989
-3.500 -0.0312 0.02806 0.01798 -0.0824 0.7279 0.1119
-3.250 -0.0234 0.02836 0.01830 -0.0799 0.7239 0.1242
-3.000 -0.0146 0.02856 0.01859 -0.0774 0.7202 0.1439
-2.750 0.0006 0.02848 0.01866 -0.0758 0.7179 0.1809
-2.500 0.0180 0.02815 0.01864 -0.0744 0.7160 0.2553
-2.250 0.0334 0.02753 0.01854 -0.0725 0.7144 0.3883
-1.750 0.0451 0.02798 0.02056 -0.0637 0.7076 0.7939
-1.500 0.0437 0.02855 0.02102 -0.0587 0.7038 0.8387
-1.250 0.0611 0.02889 0.02124 -0.0562 0.7017 0.8743
-1.000 0.0970 0.02923 0.02144 -0.0568 0.7005 0.9081
-0.750 0.1753 0.02988 0.02190 -0.0658 0.7005 0.9448
-0.500 0.3032 0.03050 0.02223 -0.0849 0.7016 0.9695
-0.250 0.3584 0.03070 0.02229 -0.0909 0.7008 0.9776
0.000 0.3949 0.03082 0.02229 -0.0932 0.6997 0.9826
0.250 0.4306 0.03087 0.02225 -0.0952 0.6987 0.9860
0.750 0.4639 0.03289 0.02424 -0.0957 0.6888 0.9988
1.000 0.4859 0.03307 0.02436 -0.0952 0.6869 1.0000
1.250 0.5044 0.03318 0.02442 -0.0939 0.6853 1.0000
1.750 0.4673 0.03492 0.02616 -0.0804 0.6728 1.0000
2.000 0.4879 0.03497 0.02616 -0.0793 0.6712 1.0000
2.500 0.4535 0.03634 0.02750 -0.0662 0.6589 1.0000
2.750 0.4749 0.03639 0.02752 -0.0652 0.6572 1.0000
3.250 0.4711 0.03778 0.02887 -0.0576 0.6456 1.0000
3.500 0.4963 0.03784 0.02892 -0.0572 0.6438 1.0000
4.000 0.5111 0.03930 0.03037 -0.0528 0.6325 1.0000
4.250 0.5371 0.03943 0.03050 -0.0527 0.6304 1.0000
4.500 0.5645 0.03956 0.03065 -0.0528 0.6290 1.0000
4.750 0.5591 0.04102 0.03212 -0.0497 0.6194 1.0000
5.000 0.5846 0.04123 0.03237 -0.0497 0.6171 1.0000
5.250 0.6133 0.04128 0.03247 -0.0499 0.6154 1.0000
5.500 0.6120 0.04273 0.03395 -0.0475 0.6058 1.0000
5.750 0.6381 0.04292 0.03420 -0.0475 0.6034 1.0000
6.000 0.6671 0.04294 0.03430 -0.0477 0.6017 1.0000
6.250 0.6671 0.04447 0.03589 -0.0457 0.5918 1.0000
6.500 0.6942 0.04456 0.03607 -0.0458 0.5893 1.0000
6.750 0.7238 0.04452 0.03613 -0.0460 0.5876 1.0000
7.000 0.7239 0.04618 0.03786 -0.0441 0.5773 1.0000
7.250 0.7516 0.04623 0.03805 -0.0443 0.5749 1.0000
7.750 0.7823 0.04785 0.03990 -0.0428 0.5623 1.0000
8.000 0.8103 0.04787 0.04008 -0.0429 0.5602 1.0000
8.250 0.8139 0.04950 0.04184 -0.0415 0.5500 1.0000
8.500 0.8413 0.04950 0.04203 -0.0415 0.5472 1.0000
8.750 0.8504 0.05062 0.04330 -0.0404 0.5374 1.0000
9.000 0.8999 0.04563 0.03851 -0.0391 0.5189 1.0000
9.250 0.9164 0.04418 0.03713 -0.0367 0.4860 1.0000
9.500 0.9436 0.04011 0.03149 -0.0320 0.2618 1.0000
9.750 0.9166 0.04423 0.03459 -0.0284 0.1305 1.0000
10.000 0.9078 0.04711 0.03683 -0.0260 0.0552 1.0000
10.250 0.9124 0.04905 0.03866 -0.0246 0.0413 1.0000
10.500 0.9210 0.05073 0.04046 -0.0235 0.0364 1.0000
10.750 0.9245 0.05287 0.04262 -0.0222 0.0320 1.0000
11.000 0.9334 0.05457 0.04449 -0.0214 0.0304 1.0000
11.250 0.9418 0.05633 0.04638 -0.0205 0.0281 1.0000
11.500 0.9494 0.05816 0.04829 -0.0197 0.0258 1.0000
11.750 0.9558 0.06006 0.05028 -0.0187 0.0245 1.0000
12.000 0.9621 0.06186 0.05211 -0.0173 0.0235 1.0000
12.250 0.9752 0.06304 0.05336 -0.0161 0.0227 1.0000
12.500 0.9919 0.06391 0.05431 -0.0149 0.0222 1.0000
12.750 1.0121 0.06455 0.05503 -0.0137 0.0214 1.0000
13.000 1.0361 0.06511 0.05570 -0.0125 0.0208 1.0000
13.250 1.0561 0.06619 0.05690 -0.0117 0.0197 1.0000
13.500 1.0742 0.06756 0.05845 -0.0110 0.0186 1.0000
13.750 1.0867 0.06934 0.06030 -0.0105 0.0175 1.0000
14.000 1.1071 0.07102 0.06216 -0.0097 0.0173 1.0000
14.250 1.1280 0.07349 0.06480 -0.0090 0.0168 1.0000
14.500 1.1361 0.07665 0.06822 -0.0082 0.0165 1.0000
14.750 1.1372 0.08008 0.07197 -0.0074 0.0164 1.0000
15.000 1.1375 0.08336 0.07549 -0.0069 0.0164 1.0000
15.250 1.1305 0.08737 0.07980 -0.0064 0.0163 1.0000
15.500 1.1216 0.09165 0.08438 -0.0061 0.0163 1.0000
15.750 1.1125 0.09595 0.08891 -0.0062 0.0163 1.0000
16.000 1.0980 0.10106 0.09431 -0.0066 0.0163 1.0000
16.250 1.0879 0.10573 0.09920 -0.0075 0.0164 1.0000
16.500 1.0725 0.11123 0.10492 -0.0088 0.0164 1.0000
16.750 1.0596 0.11673 0.11062 -0.0105 0.0165 1.0000
17.000 1.0442 0.12278 0.11687 -0.0128 0.0165 1.0000
17.250 1.0304 0.12895 0.12321 -0.0154 0.0166 1.0000
17.500 1.0092 0.13690 0.13137 -0.0195 0.0166 1.0000
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