FX 69-PR-281 (fx69pr281-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 69-PR-281 (fx69pr281-il) Reynolds number: 200,000 Max Cl/Cd: 41.14 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69pr281-il-200000.txt Download as CSV file: xf-fx69pr281-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 69-PR-281
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.4131 0.09977 0.09475 -0.1462 0.8196 0.1686
-10.250 0.4399 0.09848 0.09338 -0.1461 0.7992 0.1703
-10.000 0.3867 0.09081 0.08553 -0.1518 0.7925 0.1674
-9.750 0.4040 0.08903 0.08370 -0.1510 0.7754 0.1671
-9.500 0.4209 0.08665 0.08118 -0.1517 0.7608 0.1667
-9.250 0.4266 0.08406 0.07854 -0.1515 0.7466 0.1663
-9.000 -0.0368 0.03495 0.02885 -0.1719 0.7607 0.1913
-8.000 -0.0395 0.03199 0.02567 -0.1626 0.7161 0.1991
-7.750 -0.0705 0.02941 0.02254 -0.1600 0.7072 0.2024
-7.500 -0.0593 0.02883 0.02202 -0.1577 0.6970 0.2044
-7.250 -0.0310 0.02901 0.02226 -0.1567 0.6867 0.2062
-7.000 -0.0010 0.02916 0.02236 -0.1565 0.6771 0.2085
-6.750 0.0119 0.02891 0.02213 -0.1543 0.6672 0.2109
-6.500 0.0227 0.02812 0.02115 -0.1528 0.6583 0.2142
-6.250 0.0381 0.02708 0.01973 -0.1527 0.6503 0.2177
-6.000 0.0564 0.02683 0.01963 -0.1507 0.6417 0.2195
-5.750 0.0789 0.02676 0.01961 -0.1493 0.6330 0.2215
-5.500 0.1056 0.02662 0.01937 -0.1490 0.6252 0.2240
-5.250 0.1250 0.02631 0.01902 -0.1478 0.6176 0.2268
-5.000 0.1416 0.02571 0.01829 -0.1465 0.6096 0.2298
-4.750 0.1622 0.02509 0.01739 -0.1460 0.6022 0.2328
-4.500 0.1896 0.02470 0.01702 -0.1458 0.5949 0.2354
-4.250 0.2087 0.02457 0.01697 -0.1440 0.5869 0.2375
-4.000 0.2311 0.02437 0.01675 -0.1428 0.5787 0.2401
-3.750 0.2600 0.02421 0.01641 -0.1430 0.5710 0.2434
-3.500 0.2784 0.02390 0.01605 -0.1415 0.5632 0.2465
-3.250 0.2992 0.02363 0.01562 -0.1404 0.5552 0.2494
-3.000 0.3246 0.02306 0.01499 -0.1400 0.5477 0.2524
-2.750 0.3486 0.02299 0.01495 -0.1391 0.5401 0.2550
-2.500 0.3681 0.02289 0.01489 -0.1374 0.5320 0.2578
-2.250 0.3923 0.02277 0.01467 -0.1366 0.5243 0.2612
-2.000 0.4191 0.02268 0.01444 -0.1364 0.5165 0.2648
-1.750 0.4374 0.02251 0.01420 -0.1347 0.5082 0.2676
-1.500 0.4600 0.02211 0.01371 -0.1338 0.5004 0.2710
-1.250 0.4869 0.02209 0.01365 -0.1334 0.4927 0.2741
-1.000 0.5040 0.02204 0.01367 -0.1313 0.4849 0.2770
-0.750 0.5258 0.02199 0.01357 -0.1300 0.4773 0.2803
-0.500 0.5558 0.02208 0.01347 -0.1303 0.4696 0.2843
-0.250 0.5705 0.02201 0.01341 -0.1279 0.4621 0.2875
0.000 0.5894 0.02189 0.01320 -0.1263 0.4548 0.2905
0.250 0.6183 0.02179 0.01301 -0.1264 0.4479 0.2944
0.500 0.6312 0.02177 0.01308 -0.1236 0.4413 0.2974
0.750 0.6480 0.02179 0.01311 -0.1216 0.4346 0.3009
1.000 0.6716 0.02186 0.01307 -0.1207 0.4285 0.3050
1.250 0.6950 0.02200 0.01313 -0.1199 0.4225 0.3089
1.500 0.7117 0.02211 0.01321 -0.1179 0.4164 0.3119
1.750 0.7322 0.02202 0.01311 -0.1167 0.4109 0.3163
2.000 0.7615 0.02220 0.01319 -0.1169 0.4053 0.3209
2.250 0.7786 0.02242 0.01348 -0.1150 0.4002 0.3249
2.500 0.7967 0.02264 0.01372 -0.1134 0.3950 0.3295
2.750 0.8182 0.02286 0.01387 -0.1123 0.3903 0.3342
3.000 0.8479 0.02302 0.01389 -0.1126 0.3856 0.3395
3.250 0.8684 0.02327 0.01422 -0.1115 0.3813 0.3449
3.500 0.8846 0.02356 0.01459 -0.1097 0.3769 0.3501
3.750 0.9043 0.02384 0.01486 -0.1084 0.3726 0.3562
4.000 0.9282 0.02413 0.01505 -0.1078 0.3687 0.3622
4.250 0.9655 0.02436 0.01518 -0.1093 0.3645 0.3707
4.500 0.9764 0.02474 0.01571 -0.1068 0.3613 0.3770
4.750 0.9917 0.02513 0.01617 -0.1050 0.3575 0.3845
5.000 1.0107 0.02552 0.01652 -0.1038 0.3538 0.3920
5.250 1.0330 0.02574 0.01679 -0.1031 0.3503 0.4016
5.500 1.0672 0.02610 0.01706 -0.1041 0.3466 0.4128
5.750 1.0858 0.02667 0.01764 -0.1029 0.3436 0.4227
6.000 1.0959 0.02714 0.01828 -0.1007 0.3405 0.4331
6.250 1.1101 0.02766 0.01890 -0.0990 0.3373 0.4441
6.500 1.1283 0.02816 0.01936 -0.0978 0.3340 0.4558
6.750 1.1509 0.02848 0.01974 -0.0973 0.3309 0.4692
7.000 1.1889 0.02890 0.02002 -0.0987 0.3275 0.4857
7.250 1.1969 0.02960 0.02088 -0.0964 0.3248 0.4976
7.500 1.2016 0.03038 0.02181 -0.0938 0.3220 0.5098
7.750 1.2119 0.03112 0.02261 -0.0920 0.3191 0.5233
8.000 1.2267 0.03168 0.02328 -0.0906 0.3161 0.5388
8.250 1.2481 0.03215 0.02371 -0.0901 0.3133 0.5562
8.500 1.2799 0.03246 0.02401 -0.0906 0.3105 0.5767
8.750 1.2942 0.03332 0.02496 -0.0894 0.3079 0.5946
9.000 1.2903 0.03452 0.02637 -0.0864 0.3053 0.6111
9.250 1.2931 0.03560 0.02760 -0.0842 0.3025 0.6294
9.500 1.3029 0.03648 0.02858 -0.0827 0.2998 0.6527
9.750 1.3202 0.03705 0.02922 -0.0818 0.2973 0.6809
10.000 1.3457 0.03731 0.02953 -0.0815 0.2949 0.7178
10.250 1.3791 0.03753 0.02978 -0.0818 0.2924 0.7699
10.500 1.3557 0.03921 0.03184 -0.0768 0.2904 0.8301
10.750 1.3378 0.04076 0.03367 -0.0729 0.2880 1.0000
11.000 1.3374 0.04258 0.03553 -0.0716 0.2852 1.0000
11.250 1.3482 0.04386 0.03678 -0.0710 0.2828 1.0000
11.500 1.3694 0.04458 0.03741 -0.0710 0.2806 1.0000
11.750 1.4041 0.04467 0.03733 -0.0717 0.2785 1.0000
12.000 1.4274 0.04561 0.03819 -0.0718 0.2762 1.0000
12.250 1.3905 0.04963 0.04249 -0.0689 0.2738 1.0000
12.500 1.3595 0.05392 0.04700 -0.0671 0.2709 1.0000
12.750 1.3484 0.05708 0.05026 -0.0663 0.2682 1.0000
13.000 1.3601 0.05856 0.05171 -0.0661 0.2661 1.0000
13.250 1.3903 0.05858 0.05161 -0.0663 0.2643 1.0000
13.500 1.4347 0.05764 0.05049 -0.0669 0.2627 1.0000
13.750 1.3806 0.06471 0.05787 -0.0657 0.2597 1.0000
14.000 1.1061 0.09906 0.09326 -0.0703 0.2472 1.0000
14.250 1.1543 0.09606 0.09012 -0.0695 0.2471 1.0000
14.500 1.2080 0.09250 0.08641 -0.0685 0.2471 1.0000
14.750 1.2712 0.08800 0.08171 -0.0676 0.2472 1.0000
15.500 0.6552 0.19832 0.19380 -0.1101 0.2155 1.0000
15.750 0.6689 0.20013 0.19557 -0.1109 0.2132 1.0000
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