FX 84-W-150 (fx84w150-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 84-W-150 (fx84w150-il) Reynolds number: 500,000 Max Cl/Cd: 110.99 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w150-il-500000-n5.txt Download as CSV file: xf-fx84w150-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-150
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6528 0.07215 0.06918 -0.0844 0.9575 0.0138
-14.750 -0.7183 0.05346 0.05010 -0.1004 0.9359 0.0135
-14.250 -0.7660 0.03910 0.03516 -0.1114 0.8983 0.0136
-14.000 -0.7774 0.03564 0.03151 -0.1126 0.8856 0.0136
-13.750 -0.7846 0.03303 0.02871 -0.1126 0.8749 0.0138
-13.500 -0.7904 0.03088 0.02638 -0.1118 0.8651 0.0139
-13.250 -0.7911 0.02921 0.02455 -0.1107 0.8564 0.0141
-12.750 -0.7887 0.02656 0.02157 -0.1068 0.8415 0.0145
-12.500 -0.7845 0.02558 0.02042 -0.1044 0.8348 0.0147
-12.250 -0.7756 0.02454 0.01926 -0.1028 0.8289 0.0149
-12.000 -0.7630 0.02359 0.01822 -0.1015 0.8230 0.0152
-11.750 -0.7469 0.02283 0.01737 -0.1005 0.8179 0.0156
-11.500 -0.7286 0.02216 0.01660 -0.0997 0.8130 0.0160
-11.250 -0.7098 0.02145 0.01579 -0.0989 0.8078 0.0164
-11.000 -0.6905 0.02075 0.01496 -0.0981 0.8027 0.0168
-10.750 -0.6706 0.02005 0.01413 -0.0974 0.7982 0.0172
-10.500 -0.6493 0.01940 0.01337 -0.0969 0.7932 0.0176
-10.250 -0.6279 0.01875 0.01260 -0.0963 0.7883 0.0181
-10.000 -0.6063 0.01813 0.01190 -0.0957 0.7839 0.0186
-9.750 -0.5829 0.01763 0.01134 -0.0953 0.7794 0.0192
-9.500 -0.5589 0.01717 0.01081 -0.0950 0.7746 0.0199
-9.250 -0.5347 0.01673 0.01027 -0.0947 0.7701 0.0207
-9.000 -0.5103 0.01630 0.00972 -0.0944 0.7661 0.0214
-8.750 -0.4860 0.01578 0.00917 -0.0941 0.7615 0.0222
-8.500 -0.4609 0.01537 0.00871 -0.0939 0.7570 0.0231
-8.250 -0.4356 0.01501 0.00827 -0.0937 0.7528 0.0240
-8.000 -0.4100 0.01465 0.00783 -0.0935 0.7488 0.0250
-7.750 -0.3840 0.01429 0.00741 -0.0933 0.7442 0.0260
-7.500 -0.3583 0.01392 0.00702 -0.0932 0.7398 0.0274
-7.250 -0.3320 0.01364 0.00667 -0.0931 0.7359 0.0287
-7.000 -0.3054 0.01336 0.00632 -0.0930 0.7320 0.0301
-6.750 -0.2791 0.01302 0.00596 -0.0929 0.7275 0.0314
-6.500 -0.2525 0.01274 0.00565 -0.0928 0.7231 0.0331
-6.250 -0.2256 0.01252 0.00536 -0.0928 0.7191 0.0349
-6.000 -0.1986 0.01226 0.00507 -0.0928 0.7151 0.0369
-5.750 -0.1716 0.01201 0.00481 -0.0928 0.7107 0.0392
-5.500 -0.1443 0.01181 0.00456 -0.0928 0.7063 0.0415
-5.250 -0.1173 0.01160 0.00430 -0.0927 0.7022 0.0443
-5.000 -0.0898 0.01138 0.00410 -0.0928 0.6978 0.0475
-4.750 -0.0622 0.01121 0.00389 -0.0928 0.6931 0.0507
-4.500 -0.0349 0.01102 0.00368 -0.0928 0.6886 0.0553
-4.250 -0.0072 0.01087 0.00350 -0.0929 0.6844 0.0596
-4.000 0.0204 0.01068 0.00334 -0.0930 0.6798 0.0659
-3.750 0.0481 0.01053 0.00318 -0.0930 0.6754 0.0726
-3.500 0.0758 0.01040 0.00303 -0.0931 0.6712 0.0804
-3.250 0.1036 0.01024 0.00291 -0.0932 0.6669 0.0910
-3.000 0.1315 0.01010 0.00279 -0.0933 0.6625 0.1028
-2.750 0.1592 0.00997 0.00268 -0.0934 0.6581 0.1166
-2.500 0.1869 0.00984 0.00258 -0.0935 0.6540 0.1344
-2.250 0.2148 0.00969 0.00250 -0.0937 0.6494 0.1561
-2.000 0.2425 0.00953 0.00242 -0.0938 0.6449 0.1841
-1.750 0.2700 0.00938 0.00235 -0.0939 0.6407 0.2194
-1.500 0.2974 0.00918 0.00229 -0.0941 0.6366 0.2654
-1.250 0.3247 0.00892 0.00223 -0.0942 0.6319 0.3284
-1.000 0.3515 0.00863 0.00218 -0.0943 0.6273 0.4126
-0.500 0.4048 0.00811 0.00218 -0.0943 0.6187 0.5876
-0.250 0.4319 0.00799 0.00222 -0.0942 0.6137 0.6450
0.000 0.4590 0.00795 0.00227 -0.0941 0.6089 0.6856
0.250 0.4865 0.00795 0.00231 -0.0940 0.6042 0.7149
0.500 0.5139 0.00795 0.00237 -0.0940 0.5990 0.7410
1.000 0.5685 0.00803 0.00248 -0.0937 0.5899 0.7814
1.250 0.5954 0.00805 0.00257 -0.0935 0.5851 0.8025
1.500 0.6214 0.00810 0.00266 -0.0931 0.5800 0.8258
1.750 0.6475 0.00817 0.00273 -0.0927 0.5755 0.8413
2.000 0.6749 0.00822 0.00280 -0.0926 0.5709 0.8510
2.250 0.7017 0.00828 0.00287 -0.0925 0.5660 0.8602
2.500 0.7281 0.00837 0.00294 -0.0922 0.5611 0.8682
2.750 0.7547 0.00844 0.00302 -0.0921 0.5562 0.8766
3.000 0.7810 0.00851 0.00311 -0.0918 0.5508 0.8844
3.250 0.8066 0.00861 0.00319 -0.0914 0.5454 0.8930
3.500 0.8323 0.00868 0.00329 -0.0911 0.5399 0.9011
3.750 0.8575 0.00877 0.00339 -0.0906 0.5339 0.9102
4.000 0.8816 0.00888 0.00349 -0.0900 0.5284 0.9193
4.250 0.9067 0.00895 0.00360 -0.0895 0.5227 0.9294
4.500 0.9310 0.00904 0.00371 -0.0889 0.5170 0.9406
4.750 0.9566 0.00916 0.00383 -0.0886 0.5118 0.9530
5.000 0.9858 0.00926 0.00396 -0.0891 0.5052 0.9655
5.250 1.0172 0.00943 0.00411 -0.0902 0.4974 0.9806
5.500 1.0486 0.00956 0.00426 -0.0913 0.4887 1.0000
5.750 1.0726 0.00977 0.00444 -0.0908 0.4809 1.0000
6.000 1.0978 0.00992 0.00462 -0.0906 0.4738 1.0000
6.500 1.1454 0.01032 0.00502 -0.0897 0.4584 1.0000
6.750 1.1672 0.01058 0.00525 -0.0889 0.4498 1.0000
7.000 1.1862 0.01090 0.00552 -0.0876 0.4342 1.0000
7.250 1.2013 0.01131 0.00585 -0.0857 0.4113 1.0000
7.500 1.2117 0.01177 0.00622 -0.0828 0.3902 1.0000
7.750 1.2223 0.01228 0.00666 -0.0802 0.3710 1.0000
8.000 1.2317 0.01290 0.00719 -0.0775 0.3489 1.0000
8.250 1.2408 0.01360 0.00779 -0.0749 0.3283 1.0000
8.500 1.2500 0.01434 0.00846 -0.0725 0.3077 1.0000
8.750 1.2569 0.01525 0.00927 -0.0699 0.2846 1.0000
9.000 1.2629 0.01627 0.01018 -0.0673 0.2618 1.0000
9.250 1.2669 0.01745 0.01125 -0.0647 0.2367 1.0000
9.500 1.2702 0.01875 0.01242 -0.0621 0.2109 1.0000
9.750 1.2727 0.02016 0.01372 -0.0596 0.1868 1.0000
10.000 1.2769 0.02155 0.01501 -0.0575 0.1659 1.0000
10.250 1.2801 0.02306 0.01642 -0.0554 0.1450 1.0000
10.500 1.2819 0.02472 0.01798 -0.0533 0.1235 1.0000
10.750 1.2843 0.02641 0.01958 -0.0514 0.1052 1.0000
11.000 1.2873 0.02811 0.02122 -0.0496 0.0895 1.0000
11.250 1.2926 0.02971 0.02278 -0.0482 0.0787 1.0000
11.500 1.2979 0.03137 0.02442 -0.0469 0.0693 1.0000
11.750 1.3036 0.03305 0.02609 -0.0457 0.0615 1.0000
12.000 1.3097 0.03475 0.02779 -0.0446 0.0546 1.0000
12.250 1.3166 0.03642 0.02948 -0.0437 0.0498 1.0000
12.500 1.3220 0.03829 0.03135 -0.0428 0.0447 1.0000
12.750 1.3295 0.04002 0.03311 -0.0420 0.0410 1.0000
13.000 1.3352 0.04195 0.03506 -0.0413 0.0379 1.0000
13.250 1.3424 0.04379 0.03695 -0.0407 0.0352 1.0000
13.500 1.3486 0.04577 0.03896 -0.0402 0.0328 1.0000
13.750 1.3539 0.04789 0.04112 -0.0397 0.0308 1.0000
14.000 1.3608 0.04987 0.04316 -0.0393 0.0293 1.0000
14.250 1.3662 0.05206 0.04540 -0.0389 0.0278 1.0000
14.500 1.3702 0.05443 0.04781 -0.0386 0.0262 1.0000
14.750 1.3758 0.05669 0.05014 -0.0385 0.0251 1.0000
15.000 1.3809 0.05904 0.05256 -0.0383 0.0241 1.0000
15.250 1.3854 0.06151 0.05509 -0.0383 0.0230 1.0000
15.500 1.3886 0.06417 0.05780 -0.0383 0.0222 1.0000
15.750 1.3903 0.06707 0.06076 -0.0384 0.0214 1.0000
16.000 1.3951 0.06963 0.06341 -0.0386 0.0207 1.0000
16.250 1.3983 0.07243 0.06630 -0.0389 0.0202 1.0000
16.500 1.4015 0.07525 0.06919 -0.0392 0.0194 1.0000
16.750 1.4035 0.07829 0.07229 -0.0397 0.0187 1.0000
17.000 1.4042 0.08156 0.07563 -0.0402 0.0182 1.0000
17.250 1.4035 0.08509 0.07922 -0.0409 0.0176 1.0000
17.500 1.4058 0.08822 0.08245 -0.0416 0.0172 1.0000
17.750 1.4074 0.09148 0.08580 -0.0424 0.0167 1.0000
18.000 1.4081 0.09490 0.08932 -0.0432 0.0163 1.0000
18.250 1.4089 0.09836 0.09287 -0.0442 0.0158 1.0000
18.500 1.4088 0.10200 0.09658 -0.0453 0.0154 1.0000
18.750 1.4084 0.10569 0.10036 -0.0464 0.0151 1.0000
19.000 1.4063 0.10970 0.10443 -0.0478 0.0147 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 84-W-150 (fx84w150-il)