FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 200,000 Max Cl/Cd: 80.62 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w127-il-200000.txt Download as CSV file: xf-fx84w127-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-127
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3161 0.11662 0.11309 -0.0447 1.0000 0.0524
-11.000 -0.3281 0.11296 0.10951 -0.0504 1.0000 0.0537
-10.750 -0.3348 0.10912 0.10574 -0.0544 1.0000 0.0539
-10.500 -0.3181 0.10499 0.10161 -0.0509 1.0000 0.0554
-10.250 -0.3087 0.10307 0.09973 -0.0495 1.0000 0.0568
-10.000 -0.3230 0.10261 0.09937 -0.0459 1.0000 0.0575
-9.750 -0.3099 0.09877 0.09553 -0.0497 0.9940 0.0596
-9.500 -0.2984 0.09364 0.09040 -0.0565 0.9874 0.0628
-9.250 -0.3050 0.08349 0.08028 -0.0791 0.9756 0.0651
-9.000 -0.2875 0.07867 0.07545 -0.0781 0.9728 0.0664
-8.750 -0.2619 0.07648 0.07323 -0.0779 0.9684 0.0680
-8.500 -0.2431 0.07281 0.06954 -0.0819 0.9608 0.0703
-8.250 -0.2371 0.06732 0.06403 -0.0898 0.9480 0.0736
-8.000 -0.2521 0.06120 0.05780 -0.0974 0.9305 0.0752
-7.750 -0.3360 0.03953 0.03489 -0.1019 0.9081 0.0457
-7.500 -0.3345 0.03522 0.02995 -0.1000 0.8998 0.0451
-7.000 -0.3072 0.03014 0.02429 -0.0977 0.8852 0.0464
-6.750 -0.2898 0.02803 0.02188 -0.0966 0.8780 0.0471
-6.500 -0.2700 0.02630 0.01988 -0.0956 0.8718 0.0483
-6.250 -0.2485 0.02503 0.01832 -0.0946 0.8666 0.0509
-6.000 -0.2261 0.02380 0.01672 -0.0937 0.8594 0.0531
-5.750 -0.2036 0.02195 0.01453 -0.0927 0.8545 0.0550
-5.500 -0.1796 0.02092 0.01349 -0.0923 0.8486 0.0580
-5.250 -0.1547 0.02030 0.01275 -0.0917 0.8425 0.0621
-5.000 -0.1292 0.01953 0.01172 -0.0909 0.8382 0.0655
-4.750 -0.1050 0.01851 0.01076 -0.0905 0.8317 0.0704
-4.500 -0.0793 0.01805 0.01019 -0.0900 0.8261 0.0764
-4.250 -0.0544 0.01715 0.00928 -0.0892 0.8220 0.0825
-4.000 -0.0289 0.01686 0.00892 -0.0889 0.8151 0.0907
-3.750 -0.0041 0.01617 0.00830 -0.0883 0.8098 0.1005
-3.500 0.0215 0.01564 0.00776 -0.0877 0.8059 0.1137
-3.250 0.0462 0.01526 0.00745 -0.0874 0.7986 0.1310
-3.000 0.0716 0.01475 0.00703 -0.0870 0.7936 0.1574
-2.750 0.0969 0.01424 0.00669 -0.0865 0.7893 0.2012
-2.500 0.1204 0.01368 0.00652 -0.0862 0.7824 0.2845
-2.250 0.1422 0.01277 0.00632 -0.0854 0.7777 0.4632
-2.000 0.1615 0.01217 0.00642 -0.0834 0.7729 0.6578
-1.750 0.1822 0.01209 0.00661 -0.0813 0.7663 0.7559
-1.500 0.2044 0.01206 0.00663 -0.0792 0.7619 0.8119
-1.250 0.2260 0.01214 0.00670 -0.0771 0.7568 0.8520
-1.000 0.2469 0.01222 0.00678 -0.0750 0.7505 0.8840
-0.750 0.2705 0.01221 0.00669 -0.0732 0.7461 0.9117
-0.500 0.3002 0.01228 0.00670 -0.0729 0.7409 0.9344
-0.250 0.3384 0.01231 0.00666 -0.0745 0.7350 0.9546
0.000 0.3886 0.01227 0.00648 -0.0786 0.7308 0.9693
0.250 0.4449 0.01225 0.00636 -0.0843 0.7255 0.9803
0.500 0.5069 0.01215 0.00618 -0.0913 0.7195 0.9944
0.750 0.5468 0.01203 0.00594 -0.0940 0.7147 1.0000
1.000 0.5660 0.01212 0.00602 -0.0928 0.7080 1.0000
1.250 0.5863 0.01214 0.00600 -0.0917 0.7021 1.0000
1.500 0.6082 0.01216 0.00592 -0.0907 0.6977 1.0000
1.750 0.6263 0.01232 0.00611 -0.0893 0.6903 1.0000
2.000 0.6480 0.01236 0.00608 -0.0883 0.6851 1.0000
2.250 0.6684 0.01250 0.00620 -0.0871 0.6792 1.0000
2.500 0.6894 0.01262 0.00631 -0.0860 0.6728 1.0000
2.750 0.7140 0.01266 0.00627 -0.0853 0.6682 1.0000
3.000 0.7347 0.01286 0.00651 -0.0842 0.6607 1.0000
3.250 0.7599 0.01292 0.00653 -0.0837 0.6550 1.0000
3.500 0.7844 0.01307 0.00668 -0.0832 0.6486 1.0000
3.750 0.8094 0.01318 0.00680 -0.0828 0.6418 1.0000
4.000 0.8373 0.01326 0.00680 -0.0827 0.6367 1.0000
4.250 0.8607 0.01346 0.00709 -0.0821 0.6286 1.0000
4.500 0.8888 0.01353 0.00711 -0.0821 0.6231 1.0000
4.750 0.9129 0.01374 0.00740 -0.0816 0.6152 1.0000
5.000 0.9406 0.01380 0.00743 -0.0815 0.6086 1.0000
5.250 0.9651 0.01396 0.00767 -0.0810 0.6001 1.0000
5.500 0.9930 0.01400 0.00768 -0.0809 0.5928 1.0000
5.750 1.0170 0.01420 0.00796 -0.0804 0.5839 1.0000
6.000 1.0452 0.01427 0.00801 -0.0804 0.5769 1.0000
6.250 1.0685 0.01447 0.00832 -0.0797 0.5672 1.0000
6.500 1.0941 0.01455 0.00842 -0.0793 0.5574 1.0000
6.750 1.1177 0.01449 0.00838 -0.0783 0.5425 1.0000
7.000 1.1397 0.01449 0.00839 -0.0772 0.5256 1.0000
7.250 1.1619 0.01459 0.00852 -0.0762 0.5104 1.0000
7.500 1.1837 0.01475 0.00871 -0.0752 0.4950 1.0000
7.750 1.2044 0.01494 0.00895 -0.0740 0.4781 1.0000
8.000 1.2241 0.01519 0.00921 -0.0726 0.4598 1.0000
8.250 1.2422 0.01550 0.00951 -0.0711 0.4396 1.0000
8.500 1.2578 0.01590 0.00991 -0.0692 0.4156 1.0000
8.750 1.2704 0.01641 0.01039 -0.0669 0.3878 1.0000
9.000 1.2779 0.01710 0.01097 -0.0638 0.3546 1.0000
9.250 1.2779 0.01797 0.01170 -0.0597 0.3188 1.0000
9.750 1.2628 0.02097 0.01420 -0.0509 0.2299 1.0000
10.000 1.2503 0.02319 0.01609 -0.0469 0.1808 1.0000
10.250 1.2371 0.02577 0.01834 -0.0434 0.1353 1.0000
10.500 1.2270 0.02837 0.02071 -0.0405 0.1048 1.0000
10.750 1.2212 0.03085 0.02307 -0.0383 0.0875 1.0000
11.000 1.2183 0.03322 0.02543 -0.0364 0.0768 1.0000
11.250 1.2132 0.03587 0.02802 -0.0347 0.0699 1.0000
11.500 1.2173 0.03784 0.03008 -0.0335 0.0638 1.0000
11.750 1.2148 0.04043 0.03264 -0.0322 0.0597 1.0000
12.000 1.2186 0.04254 0.03483 -0.0311 0.0559 1.0000
12.250 1.2231 0.04462 0.03696 -0.0303 0.0522 1.0000
12.500 1.2241 0.04708 0.03938 -0.0292 0.0491 1.0000
12.750 1.2317 0.04898 0.04138 -0.0283 0.0469 1.0000
13.000 1.2399 0.05087 0.04337 -0.0276 0.0444 1.0000
13.250 1.2478 0.05281 0.04534 -0.0269 0.0422 1.0000
13.500 1.2604 0.05445 0.04688 -0.0257 0.0395 1.0000
13.750 1.2704 0.05629 0.04889 -0.0251 0.0382 1.0000
14.000 1.2816 0.05811 0.05084 -0.0245 0.0366 1.0000
14.250 1.2927 0.05999 0.05282 -0.0239 0.0351 1.0000
14.500 1.3032 0.06192 0.05482 -0.0234 0.0338 1.0000
14.750 1.3266 0.06354 0.05641 -0.0223 0.0319 1.0000
15.000 1.3273 0.06632 0.05943 -0.0221 0.0312 1.0000
15.250 1.3297 0.06927 0.06261 -0.0220 0.0304 1.0000
15.500 1.3329 0.07237 0.06594 -0.0218 0.0298 1.0000
15.750 1.3334 0.07573 0.06952 -0.0218 0.0292 1.0000
16.000 1.3320 0.07942 0.07341 -0.0221 0.0286 1.0000
16.250 1.3285 0.08343 0.07764 -0.0226 0.0283 1.0000
16.500 1.3246 0.08740 0.08179 -0.0233 0.0278 1.0000
16.750 1.3198 0.09156 0.08611 -0.0243 0.0274 1.0000
17.000 1.3126 0.09610 0.09083 -0.0257 0.0270 1.0000
17.250 1.3065 0.10058 0.09544 -0.0272 0.0266 1.0000
17.500 1.2999 0.10542 0.10041 -0.0288 0.0261 1.0000
17.750 1.2854 0.11165 0.10684 -0.0313 0.0259 1.0000
18.000 1.2675 0.11842 0.11385 -0.0347 0.0260 1.0000
18.250 1.2487 0.12577 0.12140 -0.0387 0.0259 1.0000
18.500 1.2265 0.13405 0.12993 -0.0438 0.0261 1.0000
18.750 1.0896 0.17386 0.17050 -0.0707 0.0309 1.0000
19.000 1.0681 0.18619 0.18284 -0.0779 0.0318 1.0000
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