FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 200,000 Max Cl/Cd: 54.26 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx68h120-il-200000-n5.txt Download as CSV file: xf-fx68h120-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 68-H-120
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 -0.5683 0.09147 0.08815 -0.0230 1.0000 0.0111
-11.750 -0.5922 0.08226 0.07894 -0.0284 1.0000 0.0106
-11.500 -0.6279 0.07036 0.06698 -0.0364 1.0000 0.0101
-11.250 -0.6559 0.05892 0.05539 -0.0463 1.0000 0.0098
-11.000 -0.6774 0.04990 0.04615 -0.0561 1.0000 0.0097
-10.750 -0.6945 0.04494 0.04095 -0.0597 1.0000 0.0097
-10.500 -0.7062 0.04154 0.03732 -0.0599 0.9892 0.0097
-10.250 -0.7045 0.03832 0.03374 -0.0608 0.9687 0.0100
-10.000 -0.6980 0.03572 0.03079 -0.0606 0.9586 0.0104
-9.750 -0.6882 0.03409 0.02884 -0.0595 0.9497 0.0109
-9.500 -0.6788 0.03222 0.02665 -0.0580 0.9424 0.0111
-9.250 -0.6720 0.02984 0.02400 -0.0560 0.9353 0.0116
-9.000 -0.6602 0.02807 0.02201 -0.0543 0.9302 0.0118
-8.750 -0.6456 0.02654 0.02031 -0.0529 0.9249 0.0122
-8.500 -0.6298 0.02526 0.01885 -0.0513 0.9200 0.0125
-8.250 -0.6126 0.02414 0.01758 -0.0499 0.9158 0.0130
-8.000 -0.5937 0.02304 0.01634 -0.0487 0.9114 0.0136
-7.750 -0.5745 0.02207 0.01518 -0.0474 0.9076 0.0142
-7.500 -0.5552 0.02118 0.01413 -0.0460 0.9042 0.0149
-7.250 -0.5339 0.02037 0.01317 -0.0450 0.9003 0.0158
-7.000 -0.5122 0.01964 0.01231 -0.0441 0.8964 0.0169
-6.750 -0.4917 0.01877 0.01134 -0.0429 0.8931 0.0190
-6.500 -0.4693 0.01816 0.01060 -0.0419 0.8903 0.0213
-6.250 -0.4454 0.01757 0.00986 -0.0412 0.8869 0.0239
-6.000 -0.4224 0.01680 0.00905 -0.0404 0.8831 0.0304
-5.750 -0.3992 0.01610 0.00835 -0.0396 0.8801 0.0456
-5.500 -0.3765 0.01546 0.00791 -0.0388 0.8773 0.0808
-5.250 -0.3513 0.01522 0.00771 -0.0383 0.8747 0.1079
-5.000 -0.3246 0.01511 0.00763 -0.0382 0.8711 0.1276
-4.750 -0.2981 0.01504 0.00753 -0.0379 0.8679 0.1428
-4.500 -0.2723 0.01490 0.00734 -0.0374 0.8649 0.1533
-4.250 -0.2466 0.01475 0.00708 -0.0369 0.8624 0.1616
-4.000 -0.2216 0.01452 0.00684 -0.0362 0.8567 0.1687
-3.750 -0.1978 0.01426 0.00650 -0.0350 0.8496 0.1754
-3.500 -0.1742 0.01397 0.00617 -0.0338 0.8406 0.1815
-3.250 -0.1504 0.01368 0.00583 -0.0325 0.8338 0.1888
-3.000 -0.1252 0.01344 0.00557 -0.0319 0.8258 0.1958
-2.750 -0.1001 0.01320 0.00530 -0.0311 0.8206 0.2043
-2.500 -0.0745 0.01298 0.00511 -0.0305 0.8143 0.2150
-2.250 -0.0492 0.01275 0.00489 -0.0298 0.8081 0.2276
-2.000 -0.0238 0.01252 0.00468 -0.0291 0.8017 0.2434
-1.750 0.0013 0.01226 0.00448 -0.0284 0.7941 0.2656
-1.500 0.0261 0.01197 0.00431 -0.0277 0.7863 0.2992
-1.250 0.0501 0.01161 0.00413 -0.0268 0.7782 0.3496
-1.000 0.0732 0.01123 0.00399 -0.0258 0.7682 0.4179
-0.750 0.0952 0.01078 0.00384 -0.0244 0.7571 0.5015
-0.500 0.1156 0.01028 0.00371 -0.0226 0.7445 0.6051
0.000 0.2074 0.00948 0.00368 -0.0284 0.7041 0.8798
0.250 0.2529 0.00951 0.00358 -0.0314 0.6695 0.9170
0.500 0.2866 0.00963 0.00343 -0.0321 0.6182 0.9399
0.750 0.3165 0.00997 0.00335 -0.0323 0.5514 0.9568
1.000 0.3495 0.01040 0.00343 -0.0333 0.4987 0.9695
1.250 0.3878 0.01077 0.00352 -0.0357 0.4569 0.9790
1.500 0.4442 0.01115 0.00364 -0.0419 0.4187 0.9958
1.750 0.4792 0.01139 0.00371 -0.0437 0.3926 1.0000
2.000 0.5023 0.01161 0.00380 -0.0429 0.3716 1.0000
2.250 0.5251 0.01185 0.00390 -0.0421 0.3519 1.0000
2.500 0.5480 0.01208 0.00402 -0.0414 0.3346 1.0000
2.750 0.5708 0.01231 0.00416 -0.0406 0.3190 1.0000
3.000 0.5935 0.01254 0.00431 -0.0397 0.3050 1.0000
3.250 0.6161 0.01278 0.00447 -0.0389 0.2922 1.0000
3.750 0.6610 0.01328 0.00486 -0.0371 0.2684 1.0000
4.000 0.6833 0.01354 0.00507 -0.0362 0.2576 1.0000
4.250 0.7053 0.01382 0.00529 -0.0352 0.2474 1.0000
4.500 0.7269 0.01412 0.00553 -0.0342 0.2381 1.0000
4.750 0.7490 0.01438 0.00580 -0.0332 0.2300 1.0000
5.000 0.7702 0.01471 0.00608 -0.0322 0.2232 1.0000
5.250 0.7921 0.01498 0.00637 -0.0312 0.2167 1.0000
5.500 0.8131 0.01532 0.00667 -0.0301 0.2110 1.0000
5.750 0.8345 0.01563 0.00702 -0.0290 0.2060 1.0000
6.000 0.8557 0.01595 0.00736 -0.0279 0.2012 1.0000
6.250 0.8761 0.01632 0.00772 -0.0267 0.1970 1.0000
6.500 0.8970 0.01666 0.00809 -0.0255 0.1922 1.0000
6.750 0.9172 0.01699 0.00841 -0.0244 0.1842 1.0000
7.000 0.9375 0.01729 0.00872 -0.0232 0.1737 1.0000
7.250 0.9572 0.01764 0.00906 -0.0220 0.1625 1.0000
7.500 0.9761 0.01803 0.00942 -0.0207 0.1535 1.0000
7.750 0.9954 0.01841 0.00977 -0.0194 0.1391 1.0000
8.000 1.0137 0.01888 0.01017 -0.0180 0.1189 1.0000
8.500 1.0232 0.02203 0.01262 -0.0120 0.0145 1.0000
8.750 1.0375 0.02275 0.01344 -0.0099 0.0127 1.0000
9.000 1.0508 0.02345 0.01428 -0.0078 0.0118 1.0000
9.250 1.0615 0.02420 0.01519 -0.0053 0.0112 1.0000
9.500 1.0707 0.02506 0.01620 -0.0027 0.0106 1.0000
9.750 1.0799 0.02598 0.01726 -0.0004 0.0102 1.0000
10.000 1.0869 0.02711 0.01855 0.0020 0.0097 1.0000
10.250 1.0917 0.02843 0.02004 0.0044 0.0092 1.0000
10.500 1.0925 0.03008 0.02187 0.0069 0.0084 1.0000
10.750 1.0976 0.03145 0.02339 0.0087 0.0082 1.0000
11.000 1.1002 0.03307 0.02516 0.0106 0.0079 1.0000
11.250 1.1005 0.03494 0.02718 0.0123 0.0077 1.0000
11.500 1.0990 0.03706 0.02945 0.0137 0.0076 1.0000
11.750 1.0952 0.03954 0.03208 0.0148 0.0076 1.0000
12.000 1.0885 0.04251 0.03520 0.0154 0.0073 1.0000
12.250 1.0817 0.04577 0.03860 0.0156 0.0073 1.0000
12.500 1.0722 0.04968 0.04269 0.0150 0.0072 1.0000
12.750 1.0622 0.05408 0.04723 0.0138 0.0071 1.0000
13.000 1.0509 0.05910 0.05239 0.0119 0.0071 1.0000
13.250 1.0414 0.06415 0.05758 0.0098 0.0071 1.0000
13.500 1.0308 0.06951 0.06306 0.0076 0.0072 1.0000
13.750 1.0200 0.07493 0.06858 0.0054 0.0070 1.0000
14.000 1.0118 0.07992 0.07366 0.0034 0.0069 1.0000
14.250 1.0052 0.08455 0.07836 0.0017 0.0070 1.0000
14.500 1.0001 0.08883 0.08270 0.0003 0.0068 1.0000
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