WORTMANN FX 69-274 (fx69274-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 69-274 (fx69274-il) Reynolds number: 100,000 Max Cl/Cd: 1.7 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69274-il-100000.txt Download as CSV file: xf-fx69274-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 69-274
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.2845 0.17735 0.17225 -0.0521 1.0000 0.1743
-17.000 -0.2637 0.17504 0.17002 -0.0496 0.9989 0.1755
-16.750 -0.7027 0.08504 0.07908 -0.0893 1.0000 0.1248
-16.500 -0.7123 0.08644 0.08061 -0.0850 1.0000 0.1260
-16.250 -0.7173 0.08153 0.07560 -0.0887 0.9948 0.1283
-16.000 -0.7840 0.07062 0.06421 -0.0943 0.9892 0.1286
-15.750 -0.7956 0.06543 0.05875 -0.0982 0.9832 0.1310
-15.500 -0.8142 0.05987 0.05280 -0.1021 0.9785 0.1333
-15.250 -0.8361 0.05527 0.04776 -0.1043 0.9702 0.1352
-15.000 -0.7712 0.05486 0.04767 -0.1082 0.9661 0.1410
-14.750 -0.7698 0.05182 0.04440 -0.1103 0.9578 0.1448
-14.500 -0.7618 0.04911 0.04147 -0.1120 0.9499 0.1488
-14.250 -0.7272 0.04846 0.04098 -0.1133 0.9410 0.1544
-14.000 -0.7285 0.04621 0.03848 -0.1133 0.9320 0.1588
-13.750 -0.7073 0.04534 0.03770 -0.1131 0.9219 0.1642
-13.500 -0.6956 0.04422 0.03654 -0.1125 0.9136 0.1701
-13.250 -0.7039 0.04260 0.03469 -0.1106 0.9021 0.1749
-13.000 -0.6765 0.04224 0.03455 -0.1100 0.8947 0.1822
-12.750 -0.6816 0.04090 0.03300 -0.1082 0.8839 0.1881
-12.500 -0.6600 0.04036 0.03264 -0.1073 0.8766 0.1959
-12.250 -0.6619 0.03926 0.03139 -0.1055 0.8678 0.2032
-12.000 -0.6441 0.03872 0.03101 -0.1046 0.8599 0.2119
-11.750 -0.6481 0.03761 0.02970 -0.1017 0.8534 0.2202
-11.500 -0.6294 0.03728 0.02959 -0.1013 0.8444 0.2301
-11.250 -0.6273 0.03640 0.02864 -0.0990 0.8367 0.2399
-11.000 -0.6189 0.03582 0.02810 -0.0966 0.8313 0.2506
-10.750 -0.6117 0.03551 0.02789 -0.0953 0.8221 0.2614
-10.500 -0.6172 0.03485 0.02709 -0.0919 0.8148 0.2726
-10.250 -0.6030 0.03447 0.02686 -0.0899 0.8099 0.2857
-10.000 -0.6052 0.03454 0.02699 -0.0867 0.8007 0.2968
-9.750 -0.6130 0.03446 0.02687 -0.0820 0.7931 0.3083
-9.500 -0.6010 0.03428 0.02679 -0.0794 0.7883 0.3223
-9.250 -0.6055 0.03455 0.02705 -0.0753 0.7808 0.3340
-9.000 -0.6094 0.03494 0.02746 -0.0712 0.7724 0.3458
-8.750 -0.5922 0.03486 0.02746 -0.0693 0.7677 0.3602
-8.500 -0.5768 0.03458 0.02713 -0.0671 0.7640 0.3750
-8.250 -0.5889 0.03560 0.02821 -0.0622 0.7531 0.3840
-8.000 -0.5768 0.03572 0.02834 -0.0598 0.7472 0.3966
-7.750 -0.5676 0.03545 0.02791 -0.0569 0.7434 0.4112
-7.500 -0.5264 0.03553 0.02811 -0.0580 0.7410 0.4257
-7.250 -0.5699 0.03695 0.02948 -0.0494 0.7275 0.4312
-7.000 -0.5329 0.03721 0.02989 -0.0501 0.7234 0.4440
-6.750 -0.5053 0.03699 0.02960 -0.0495 0.7204 0.4580
-6.500 -0.4740 0.03685 0.02938 -0.0493 0.7182 0.4725
-6.250 -0.5371 0.03902 0.03157 -0.0389 0.7036 0.4750
-6.000 -0.4921 0.03951 0.03222 -0.0403 0.7001 0.4866
-5.750 -0.4585 0.03922 0.03184 -0.0405 0.6976 0.5001
-5.500 -0.4965 0.04118 0.03389 -0.0328 0.6873 0.5040
-5.250 -0.5012 0.04175 0.03440 -0.0288 0.6806 0.5138
-5.000 -0.4618 0.04187 0.03452 -0.0298 0.6773 0.5248
-4.750 -0.4245 0.04145 0.03396 -0.0307 0.6750 0.5391
-4.500 -0.4696 0.04347 0.03604 -0.0226 0.6645 0.5428
-4.250 -0.4522 0.04443 0.03710 -0.0211 0.6589 0.5510
-4.000 -0.4250 0.04433 0.03689 -0.0209 0.6555 0.5645
-3.750 -0.3784 0.04483 0.03746 -0.0219 0.6532 0.5746
-3.500 -0.4034 0.04617 0.03868 -0.0173 0.6464 0.5849
-3.250 -0.4071 0.04790 0.04054 -0.0141 0.6394 0.5901
-3.000 -0.3806 0.04835 0.04098 -0.0136 0.6353 0.5994
-2.750 -0.3452 0.04800 0.04052 -0.0143 0.6324 0.6107
-2.500 -0.2995 0.04803 0.04056 -0.0151 0.6305 0.6190
-2.250 -0.3538 0.05128 0.04385 -0.0090 0.6208 0.6258
-2.000 -0.3427 0.05216 0.04471 -0.0078 0.6166 0.6343
-1.750 -0.3178 0.05289 0.04546 -0.0071 0.6134 0.6423
-1.500 -0.2818 0.05264 0.04508 -0.0080 0.6108 0.6550
-1.250 -0.2361 0.05269 0.04515 -0.0083 0.6089 0.6624
-1.000 -0.2955 0.05653 0.04910 -0.0025 0.5997 0.6682
-0.750 -0.2876 0.05765 0.05016 -0.0019 0.5967 0.6787
-0.500 -0.3633 0.06471 0.05748 0.0015 0.6387 0.6810
-0.250 -0.3592 0.06666 0.05949 0.0029 0.6437 0.6881
0.000 -0.3444 0.06739 0.06012 0.0027 0.6389 0.7003
0.250 -0.3260 0.06859 0.06139 0.0040 0.6356 0.7067
0.500 -0.2866 0.07000 0.06274 0.0028 0.6318 0.7171
0.750 -0.2569 0.06771 0.06034 0.0050 0.5948 0.7275
1.000 -0.2334 0.06874 0.06138 0.0057 0.5918 0.7359
1.250 -0.2108 0.06995 0.06252 0.0050 0.5903 0.7479
1.500 -0.1916 0.07145 0.06407 0.0062 0.5892 0.7551
1.750 -0.1664 0.07306 0.06563 0.0059 0.5883 0.7662
2.000 -0.1412 0.07490 0.06747 0.0060 0.5874 0.7753
2.250 -0.2242 0.07779 0.07057 0.0119 0.6010 0.7798
2.500 -0.2044 0.07865 0.07137 0.0118 0.5943 0.7915
2.750 -0.1789 0.07992 0.07265 0.0125 0.5910 0.8001
3.000 -0.1433 0.08186 0.07454 0.0114 0.5888 0.8117
3.250 -0.1012 0.08466 0.07731 0.0102 0.5875 0.8213
3.500 -0.1621 0.08340 0.07615 0.0167 0.5770 0.8285
3.750 -0.1389 0.08444 0.07716 0.0167 0.5722 0.8392
4.000 -0.1098 0.08594 0.07864 0.0170 0.5694 0.8500
4.250 -0.0728 0.08827 0.08094 0.0161 0.5678 0.8613
4.500 -0.1155 0.08822 0.08096 0.0207 0.5604 0.8701
4.750 -0.1030 0.08905 0.08180 0.0218 0.5546 0.8811
5.000 -0.0794 0.09024 0.08295 0.0220 0.5510 0.8940
5.250 -0.0494 0.09193 0.08462 0.0220 0.5488 0.9070
5.500 -0.0104 0.09471 0.08737 0.0210 0.5474 0.9201
5.750 -0.0601 0.09392 0.08668 0.0255 0.5376 0.9304
6.000 -0.0368 0.09532 0.08807 0.0247 0.5330 0.9436
6.250 0.0008 0.09745 0.09019 0.0220 0.5299 0.9559
6.500 0.0542 0.10096 0.09368 0.0171 0.5280 0.9661
6.750 0.0313 0.10216 0.09496 0.0168 0.5196 0.9726
7.000 0.0658 0.10449 0.09729 0.0126 0.5137 0.9807
7.250 0.1162 0.10758 0.10037 0.0068 0.5103 0.9856
7.500 0.1760 0.11176 0.10454 0.0003 0.5084 0.9920
7.750 0.1508 0.11324 0.10610 -0.0006 0.4993 0.9984
8.000 0.1528 0.11288 0.10568 0.0013 0.4945 1.0000
8.250 0.1636 0.11296 0.10568 0.0028 0.4915 1.0000
8.500 0.1959 0.11522 0.10788 0.0012 0.4897 1.0000
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