FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 500,000 Max Cl/Cd: 115.68 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w127-il-500000.txt Download as CSV file: xf-fx84w127-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3179 0.09776 0.09556 -0.0566 0.9728 0.0294
-10.500 -0.4893 0.04597 0.04346 -0.0938 0.9296 0.0188
-10.250 -0.5256 0.04134 0.03857 -0.0937 0.9056 0.0186
-10.000 -0.5578 0.03664 0.03347 -0.0914 0.8900 0.0185
-9.750 -0.5731 0.03204 0.02834 -0.0895 0.8794 0.0187
-9.500 -0.5723 0.02870 0.02453 -0.0879 0.8710 0.0190
-9.250 -0.5618 0.02637 0.02179 -0.0867 0.8639 0.0193
-9.000 -0.5508 0.02360 0.01860 -0.0856 0.8570 0.0197
-8.750 -0.5319 0.02223 0.01708 -0.0849 0.8514 0.0204
-8.500 -0.5086 0.02160 0.01640 -0.0846 0.8451 0.0211
-8.250 -0.4856 0.02093 0.01559 -0.0842 0.8396 0.0220
-8.000 -0.4628 0.01994 0.01440 -0.0837 0.8342 0.0229
-7.750 -0.4390 0.01901 0.01324 -0.0833 0.8282 0.0237
-7.500 -0.4168 0.01759 0.01158 -0.0827 0.8233 0.0245
-7.250 -0.3926 0.01667 0.01061 -0.0824 0.8181 0.0255
-7.000 -0.3669 0.01617 0.01005 -0.0822 0.8124 0.0266
-6.750 -0.3411 0.01570 0.00947 -0.0819 0.8075 0.0280
-6.500 -0.3144 0.01535 0.00899 -0.0818 0.8024 0.0293
-6.250 -0.2902 0.01427 0.00783 -0.0814 0.7970 0.0310
-6.000 -0.2640 0.01385 0.00737 -0.0812 0.7923 0.0327
-5.750 -0.2373 0.01348 0.00692 -0.0811 0.7872 0.0346
-5.500 -0.2102 0.01315 0.00651 -0.0809 0.7817 0.0365
-5.250 -0.1848 0.01249 0.00583 -0.0807 0.7769 0.0395
-5.000 -0.1576 0.01220 0.00550 -0.0806 0.7719 0.0423
-4.750 -0.1305 0.01185 0.00508 -0.0805 0.7663 0.0450
-4.500 -0.1040 0.01144 0.00465 -0.0803 0.7614 0.0495
-4.250 -0.0763 0.01125 0.00442 -0.0803 0.7564 0.0535
-4.000 -0.0494 0.01083 0.00401 -0.0803 0.7509 0.0597
-3.750 -0.0216 0.01069 0.00380 -0.0802 0.7461 0.0653
-3.500 0.0056 0.01036 0.00350 -0.0802 0.7411 0.0751
-3.250 0.0332 0.01010 0.00327 -0.0802 0.7357 0.0871
-3.000 0.0608 0.00988 0.00306 -0.0802 0.7308 0.1031
-2.750 0.0884 0.00965 0.00289 -0.0803 0.7259 0.1261
-2.500 0.1160 0.00940 0.00275 -0.0804 0.7205 0.1593
-2.250 0.1434 0.00913 0.00262 -0.0805 0.7156 0.2054
-2.000 0.1706 0.00882 0.00251 -0.0806 0.7107 0.2720
-1.750 0.1973 0.00839 0.00242 -0.0807 0.7052 0.3729
-1.500 0.2228 0.00784 0.00234 -0.0805 0.7003 0.5221
-1.250 0.2481 0.00746 0.00236 -0.0801 0.6952 0.6505
-1.000 0.2742 0.00729 0.00240 -0.0796 0.6896 0.7255
-0.750 0.3006 0.00723 0.00242 -0.0791 0.6846 0.7734
-0.500 0.3270 0.00722 0.00246 -0.0786 0.6791 0.8075
-0.250 0.3536 0.00721 0.00248 -0.0781 0.6733 0.8341
0.000 0.3797 0.00724 0.00249 -0.0775 0.6683 0.8552
0.250 0.4056 0.00725 0.00254 -0.0769 0.6627 0.8741
0.500 0.4310 0.00727 0.00256 -0.0762 0.6572 0.8919
0.750 0.4558 0.00733 0.00257 -0.0753 0.6525 0.9090
1.000 0.4800 0.00733 0.00261 -0.0743 0.6468 0.9255
1.250 0.5042 0.00735 0.00262 -0.0733 0.6412 0.9411
1.500 0.5303 0.00739 0.00262 -0.0726 0.6362 0.9597
1.750 0.5671 0.00741 0.00266 -0.0743 0.6303 0.9760
2.000 0.6061 0.00746 0.00266 -0.0767 0.6246 0.9843
2.250 0.6465 0.00752 0.00269 -0.0795 0.6186 0.9884
2.500 0.6851 0.00755 0.00271 -0.0819 0.6119 0.9936
2.750 0.7242 0.00763 0.00272 -0.0845 0.6059 0.9982
3.000 0.7519 0.00766 0.00278 -0.0848 0.5992 1.0000
3.250 0.7728 0.00776 0.00283 -0.0836 0.5933 1.0000
3.500 0.7949 0.00784 0.00293 -0.0826 0.5872 1.0000
3.750 0.8184 0.00794 0.00301 -0.0820 0.5807 1.0000
4.000 0.8435 0.00806 0.00310 -0.0816 0.5745 1.0000
4.250 0.8693 0.00815 0.00320 -0.0813 0.5665 1.0000
4.500 0.8954 0.00827 0.00330 -0.0811 0.5589 1.0000
4.750 0.9218 0.00838 0.00342 -0.0810 0.5509 1.0000
5.000 0.9482 0.00853 0.00356 -0.0808 0.5439 1.0000
5.250 0.9747 0.00865 0.00370 -0.0807 0.5358 1.0000
5.500 1.0010 0.00880 0.00385 -0.0806 0.5278 1.0000
5.750 1.0265 0.00896 0.00399 -0.0803 0.5166 1.0000
6.000 1.0510 0.00912 0.00413 -0.0798 0.4997 1.0000
6.250 1.0756 0.00930 0.00429 -0.0794 0.4830 1.0000
6.500 1.1001 0.00951 0.00449 -0.0789 0.4680 1.0000
6.750 1.1241 0.00975 0.00471 -0.0785 0.4523 1.0000
7.000 1.1476 0.01002 0.00496 -0.0779 0.4354 1.0000
7.250 1.1701 0.01034 0.00524 -0.0772 0.4160 1.0000
7.500 1.1909 0.01073 0.00556 -0.0762 0.3930 1.0000
7.750 1.2098 0.01122 0.00595 -0.0749 0.3657 1.0000
8.000 1.2265 0.01180 0.00640 -0.0734 0.3336 1.0000
8.250 1.2395 0.01254 0.00696 -0.0712 0.2944 1.0000
8.500 1.2474 0.01348 0.00766 -0.0684 0.2508 1.0000
8.750 1.2486 0.01451 0.00846 -0.0644 0.2088 1.0000
9.000 1.2492 0.01566 0.00939 -0.0607 0.1707 1.0000
9.250 1.2485 0.01700 0.01050 -0.0571 0.1322 1.0000
9.500 1.2485 0.01842 0.01173 -0.0539 0.0990 1.0000
9.750 1.2509 0.01981 0.01299 -0.0512 0.0763 1.0000
10.000 1.2549 0.02119 0.01428 -0.0489 0.0611 1.0000
10.250 1.2614 0.02248 0.01554 -0.0470 0.0518 1.0000
10.500 1.2688 0.02377 0.01685 -0.0452 0.0456 1.0000
10.750 1.2742 0.02526 0.01833 -0.0435 0.0409 1.0000
11.000 1.2825 0.02658 0.01971 -0.0420 0.0374 1.0000
11.250 1.2901 0.02799 0.02115 -0.0407 0.0345 1.0000
11.500 1.2904 0.03004 0.02323 -0.0389 0.0319 1.0000
11.750 1.3002 0.03139 0.02466 -0.0379 0.0306 1.0000
12.000 1.3077 0.03296 0.02630 -0.0369 0.0290 1.0000
12.250 1.3129 0.03477 0.02815 -0.0358 0.0274 1.0000
12.500 1.3108 0.03728 0.03072 -0.0346 0.0260 1.0000
12.750 1.3150 0.03931 0.03284 -0.0337 0.0251 1.0000
13.000 1.3229 0.04106 0.03466 -0.0331 0.0239 1.0000
13.250 1.3282 0.04310 0.03677 -0.0325 0.0230 1.0000
13.500 1.3331 0.04524 0.03896 -0.0320 0.0220 1.0000
13.750 1.3341 0.04786 0.04163 -0.0315 0.0213 1.0000
14.000 1.3275 0.05132 0.04517 -0.0309 0.0205 1.0000
14.250 1.3336 0.05353 0.04747 -0.0307 0.0200 1.0000
14.500 1.3387 0.05590 0.04994 -0.0306 0.0194 1.0000
14.750 1.3431 0.05838 0.05251 -0.0305 0.0188 1.0000
15.000 1.3481 0.06085 0.05505 -0.0307 0.0181 1.0000
15.250 1.3504 0.06368 0.05794 -0.0308 0.0175 1.0000
15.500 1.3526 0.06658 0.06090 -0.0310 0.0170 1.0000
15.750 1.3519 0.06982 0.06419 -0.0313 0.0164 1.0000
16.000 1.3518 0.07300 0.06746 -0.0313 0.0160 1.0000
16.250 1.3554 0.07587 0.07045 -0.0317 0.0158 1.0000
16.500 1.3588 0.07886 0.07355 -0.0323 0.0154 1.0000
16.750 1.3610 0.08204 0.07684 -0.0329 0.0150 1.0000
17.000 1.3628 0.08530 0.08021 -0.0337 0.0147 1.0000
17.250 1.3644 0.08864 0.08365 -0.0345 0.0144 1.0000
17.500 1.3654 0.09214 0.08725 -0.0356 0.0140 1.0000
17.750 1.3659 0.09576 0.09095 -0.0367 0.0137 1.0000
18.000 1.3664 0.09939 0.09466 -0.0379 0.0135 1.0000
18.250 1.3662 0.10311 0.09845 -0.0392 0.0132 1.0000
18.500 1.3654 0.10684 0.10225 -0.0403 0.0129 1.0000
18.750 1.3608 0.11125 0.10681 -0.0416 0.0125 1.0000
19.000 1.3572 0.11593 0.11164 -0.0438 0.0124 1.0000
19.250 1.3528 0.12079 0.11666 -0.0461 0.0122 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 84-W-127 (fx84w127-il)