FX 84-W-175 (fx84w175-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-175 (fx84w175-il) Reynolds number: 200,000 Max Cl/Cd: 69.76 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w175-il-200000-n5.txt Download as CSV file: xf-fx84w175-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-175
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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5139 0.06129 0.05653 -0.1190 0.9191 0.0312
-14.000 -0.5443 0.05349 0.04842 -0.1251 0.9091 0.0312
-13.750 -0.5665 0.04811 0.04276 -0.1283 0.8986 0.0313
-13.500 -0.5840 0.04399 0.03835 -0.1300 0.8895 0.0316
-13.250 -0.5962 0.04086 0.03496 -0.1304 0.8809 0.0318
-13.000 -0.5964 0.03893 0.03290 -0.1301 0.8740 0.0321
-12.750 -0.5940 0.03736 0.03128 -0.1296 0.8665 0.0324
-12.500 -0.5918 0.03588 0.02969 -0.1286 0.8604 0.0328
-12.250 -0.5885 0.03452 0.02822 -0.1277 0.8536 0.0333
-12.000 -0.5852 0.03321 0.02678 -0.1264 0.8472 0.0338
-11.750 -0.5818 0.03194 0.02533 -0.1247 0.8419 0.0344
-11.500 -0.5769 0.03076 0.02399 -0.1231 0.8354 0.0351
-11.250 -0.5721 0.02959 0.02262 -0.1211 0.8295 0.0359
-11.000 -0.5662 0.02858 0.02136 -0.1187 0.8249 0.0366
-10.750 -0.5533 0.02777 0.02053 -0.1174 0.8198 0.0372
-10.500 -0.5390 0.02702 0.01973 -0.1162 0.8144 0.0379
-10.250 -0.5237 0.02627 0.01889 -0.1150 0.8100 0.0387
-10.000 -0.5071 0.02552 0.01799 -0.1138 0.8063 0.0397
-9.750 -0.4895 0.02479 0.01712 -0.1129 0.8013 0.0410
-9.500 -0.4712 0.02405 0.01626 -0.1119 0.7964 0.0422
-9.250 -0.4522 0.02344 0.01562 -0.1110 0.7923 0.0433
-9.000 -0.4321 0.02286 0.01495 -0.1102 0.7889 0.0446
-8.750 -0.4115 0.02228 0.01429 -0.1095 0.7844 0.0460
-8.500 -0.3902 0.02170 0.01358 -0.1088 0.7797 0.0477
-8.250 -0.3693 0.02113 0.01300 -0.1081 0.7756 0.0492
-8.000 -0.3471 0.02066 0.01246 -0.1075 0.7722 0.0511
-7.750 -0.3246 0.02020 0.01191 -0.1069 0.7682 0.0533
-7.500 -0.3025 0.01970 0.01138 -0.1063 0.7636 0.0553
-7.250 -0.2797 0.01928 0.01093 -0.1057 0.7595 0.0575
-7.000 -0.2560 0.01887 0.01043 -0.1052 0.7559 0.0604
-6.750 -0.2325 0.01844 0.00995 -0.1048 0.7525 0.0634
-6.500 -0.2092 0.01810 0.00962 -0.1043 0.7479 0.0666
-6.250 -0.1849 0.01779 0.00922 -0.1039 0.7436 0.0704
-6.000 -0.1611 0.01739 0.00884 -0.1034 0.7398 0.0744
-5.750 -0.1357 0.01708 0.00843 -0.1031 0.7367 0.0793
-5.500 -0.1119 0.01677 0.00816 -0.1027 0.7323 0.0843
-5.250 -0.0871 0.01653 0.00788 -0.1024 0.7279 0.0905
-5.000 -0.0624 0.01621 0.00758 -0.1020 0.7239 0.0971
-4.750 -0.0365 0.01594 0.00726 -0.1018 0.7206 0.1050
-4.500 -0.0112 0.01570 0.00702 -0.1016 0.7170 0.1143
-4.250 0.0134 0.01547 0.00684 -0.1012 0.7123 0.1248
-4.000 0.0388 0.01524 0.00662 -0.1010 0.7082 0.1371
-3.750 0.0648 0.01499 0.00639 -0.1008 0.7046 0.1524
-3.500 0.0914 0.01475 0.00615 -0.1008 0.7016 0.1709
-3.250 0.1158 0.01456 0.00606 -0.1004 0.6969 0.1928
-3.000 0.1409 0.01433 0.00592 -0.1002 0.6925 0.2198
-2.750 0.1666 0.01406 0.00575 -0.1000 0.6887 0.2539
-2.500 0.1927 0.01375 0.00556 -0.0999 0.6855 0.2989
-2.250 0.2167 0.01347 0.00550 -0.0996 0.6813 0.3557
-2.000 0.2402 0.01315 0.00546 -0.0991 0.6767 0.4272
-1.750 0.2645 0.01286 0.00544 -0.0986 0.6727 0.5035
-1.500 0.2902 0.01267 0.00543 -0.0981 0.6694 0.5690
-1.250 0.3156 0.01262 0.00549 -0.0976 0.6656 0.6181
-1.000 0.3403 0.01264 0.00561 -0.0969 0.6608 0.6544
-0.750 0.3660 0.01266 0.00567 -0.0964 0.6566 0.6833
-0.500 0.3930 0.01268 0.00568 -0.0960 0.6531 0.7080
-0.250 0.4196 0.01274 0.00572 -0.0957 0.6495 0.7291
0.000 0.4439 0.01283 0.00586 -0.0950 0.6446 0.7470
0.250 0.4692 0.01291 0.00594 -0.0944 0.6402 0.7631
0.500 0.4955 0.01296 0.00597 -0.0939 0.6365 0.7781
0.750 0.5213 0.01304 0.00602 -0.0933 0.6329 0.7943
1.000 0.5436 0.01317 0.00620 -0.0922 0.6279 0.8109
1.250 0.5675 0.01327 0.00630 -0.0913 0.6235 0.8256
1.500 0.5930 0.01332 0.00633 -0.0907 0.6198 0.8356
1.750 0.6192 0.01338 0.00635 -0.0904 0.6160 0.8446
2.000 0.6414 0.01349 0.00650 -0.0894 0.6110 0.8531
2.250 0.6657 0.01357 0.00657 -0.0888 0.6065 0.8619
2.500 0.6911 0.01362 0.00658 -0.0883 0.6027 0.8697
2.750 0.7162 0.01370 0.00664 -0.0878 0.5985 0.8783
3.000 0.7371 0.01381 0.00680 -0.0866 0.5935 0.8866
3.250 0.7607 0.01389 0.00687 -0.0859 0.5889 0.8956
3.500 0.7860 0.01393 0.00689 -0.0854 0.5850 0.9038
3.750 0.8084 0.01404 0.00702 -0.0845 0.5804 0.9132
4.000 0.8301 0.01416 0.00718 -0.0835 0.5752 0.9234
4.250 0.8557 0.01423 0.00725 -0.0832 0.5707 0.9328
4.500 0.8843 0.01431 0.00728 -0.0834 0.5668 0.9427
4.750 0.9095 0.01449 0.00754 -0.0834 0.5610 0.9544
5.000 0.9410 0.01464 0.00772 -0.0845 0.5559 0.9651
5.250 0.9765 0.01475 0.00779 -0.0864 0.5514 0.9754
5.750 1.0297 0.01516 0.00827 -0.0872 0.5405 1.0000
6.000 1.0534 0.01531 0.00839 -0.0868 0.5358 1.0000
6.250 1.0740 0.01553 0.00863 -0.0860 0.5305 1.0000
6.500 1.0917 0.01579 0.00892 -0.0846 0.5245 1.0000
6.750 1.1140 0.01597 0.00908 -0.0839 0.5192 1.0000
7.000 1.1306 0.01625 0.00938 -0.0823 0.5130 1.0000
7.250 1.1467 0.01656 0.00972 -0.0807 0.5065 1.0000
7.500 1.1694 0.01677 0.00989 -0.0801 0.5010 1.0000
7.750 1.1815 0.01721 0.01040 -0.0780 0.4940 1.0000
8.000 1.1995 0.01754 0.01073 -0.0768 0.4875 1.0000
8.250 1.2165 0.01792 0.01114 -0.0755 0.4811 1.0000
8.500 1.2305 0.01839 0.01166 -0.0738 0.4739 1.0000
8.750 1.2501 0.01873 0.01196 -0.0729 0.4676 1.0000
9.000 1.2605 0.01936 0.01268 -0.0708 0.4597 1.0000
9.250 1.2770 0.01981 0.01312 -0.0696 0.4524 1.0000
9.500 1.2874 0.02050 0.01388 -0.0676 0.4441 1.0000
9.750 1.3014 0.02105 0.01440 -0.0661 0.4352 1.0000
10.000 1.3075 0.02195 0.01536 -0.0638 0.4238 1.0000
10.250 1.3148 0.02285 0.01625 -0.0617 0.4117 1.0000
10.500 1.3218 0.02381 0.01719 -0.0596 0.3992 1.0000
10.750 1.3283 0.02486 0.01822 -0.0577 0.3867 1.0000
11.000 1.3344 0.02602 0.01940 -0.0558 0.3741 1.0000
11.250 1.3400 0.02725 0.02064 -0.0539 0.3614 1.0000
11.500 1.3449 0.02857 0.02196 -0.0521 0.3483 1.0000
11.750 1.3484 0.03003 0.02340 -0.0503 0.3346 1.0000
12.000 1.3509 0.03164 0.02498 -0.0485 0.3203 1.0000
12.250 1.3524 0.03341 0.02671 -0.0468 0.3055 1.0000
12.500 1.3529 0.03533 0.02861 -0.0452 0.2903 1.0000
12.750 1.3528 0.03739 0.03064 -0.0437 0.2748 1.0000
13.000 1.3514 0.03965 0.03286 -0.0423 0.2587 1.0000
13.250 1.3495 0.04204 0.03521 -0.0409 0.2426 1.0000
13.500 1.3470 0.04459 0.03771 -0.0398 0.2268 1.0000
13.750 1.3445 0.04723 0.04032 -0.0387 0.2119 1.0000
14.000 1.3412 0.05005 0.04310 -0.0378 0.1967 1.0000
14.250 1.3381 0.05293 0.04595 -0.0371 0.1822 1.0000
14.500 1.3348 0.05593 0.04892 -0.0365 0.1679 1.0000
14.750 1.3323 0.05895 0.05192 -0.0360 0.1546 1.0000
15.000 1.3289 0.06213 0.05507 -0.0357 0.1413 1.0000
15.250 1.3263 0.06532 0.05825 -0.0354 0.1292 1.0000
15.500 1.3236 0.06859 0.06150 -0.0354 0.1180 1.0000
15.750 1.3214 0.07186 0.06478 -0.0354 0.1082 1.0000
16.000 1.3185 0.07530 0.06821 -0.0355 0.0995 1.0000
16.250 1.3163 0.07871 0.07164 -0.0358 0.0918 1.0000
16.500 1.3158 0.08198 0.07494 -0.0361 0.0849 1.0000
16.750 1.3133 0.08555 0.07852 -0.0366 0.0792 1.0000
17.000 1.3136 0.08881 0.08183 -0.0371 0.0737 1.0000
17.250 1.3118 0.09239 0.08545 -0.0377 0.0694 1.0000
17.500 1.3122 0.09571 0.08883 -0.0384 0.0649 1.0000
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Polar data table (+)
Polar graphs
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