FX 84-W-140 (fx84w140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 84-W-140 (fx84w140-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.43 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w140-il-1000000-n5.txt Download as CSV file: xf-fx84w140-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-140
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6262 0.09679 0.09465 -0.0633 0.9689 0.0092
-15.500 -0.8984 0.04115 0.03806 -0.1064 0.9260 0.0085
-15.250 -0.9266 0.03531 0.03193 -0.1096 0.9007 0.0084
-15.000 -0.9398 0.03216 0.02859 -0.1100 0.8852 0.0085
-14.750 -0.9483 0.02982 0.02609 -0.1093 0.8729 0.0085
-14.500 -0.9536 0.02800 0.02412 -0.1078 0.8627 0.0086
-14.250 -0.9554 0.02660 0.02260 -0.1058 0.8532 0.0087
-14.000 -0.9554 0.02546 0.02135 -0.1032 0.8455 0.0088
-13.750 -0.9492 0.02450 0.02026 -0.1011 0.8381 0.0089
-13.500 -0.9377 0.02353 0.01918 -0.0998 0.8320 0.0090
-13.250 -0.9229 0.02267 0.01822 -0.0987 0.8260 0.0092
-13.000 -0.9072 0.02183 0.01726 -0.0977 0.8205 0.0093
-12.750 -0.8894 0.02107 0.01639 -0.0969 0.8157 0.0095
-12.500 -0.8706 0.02032 0.01555 -0.0962 0.8103 0.0097
-12.250 -0.8509 0.01963 0.01475 -0.0955 0.8048 0.0099
-12.000 -0.8301 0.01898 0.01399 -0.0949 0.8002 0.0101
-11.750 -0.8081 0.01841 0.01333 -0.0945 0.7953 0.0102
-11.500 -0.7858 0.01785 0.01267 -0.0940 0.7903 0.0104
-11.250 -0.7645 0.01712 0.01185 -0.0935 0.7856 0.0108
-11.000 -0.7413 0.01655 0.01121 -0.0932 0.7808 0.0111
-10.750 -0.7174 0.01605 0.01065 -0.0929 0.7759 0.0114
-10.250 -0.6684 0.01514 0.00959 -0.0924 0.7669 0.0120
-10.000 -0.6433 0.01471 0.00909 -0.0922 0.7621 0.0124
-9.750 -0.6180 0.01432 0.00862 -0.0920 0.7575 0.0127
-9.500 -0.5924 0.01395 0.00817 -0.0919 0.7533 0.0130
-9.250 -0.5667 0.01353 0.00769 -0.0918 0.7489 0.0134
-9.000 -0.5409 0.01313 0.00724 -0.0916 0.7441 0.0140
-8.500 -0.4881 0.01248 0.00651 -0.0915 0.7360 0.0151
-8.250 -0.4612 0.01221 0.00618 -0.0915 0.7314 0.0158
-8.000 -0.4342 0.01195 0.00586 -0.0915 0.7268 0.0163
-7.750 -0.4076 0.01163 0.00550 -0.0914 0.7227 0.0172
-7.500 -0.3804 0.01135 0.00521 -0.0915 0.7187 0.0180
-7.250 -0.3530 0.01112 0.00493 -0.0915 0.7145 0.0189
-7.000 -0.3256 0.01091 0.00466 -0.0915 0.7100 0.0197
-6.750 -0.2982 0.01066 0.00439 -0.0916 0.7060 0.0209
-6.500 -0.2705 0.01044 0.00416 -0.0917 0.7015 0.0223
-6.250 -0.2427 0.01026 0.00394 -0.0918 0.6971 0.0235
-5.750 -0.1872 0.00987 0.00350 -0.0919 0.6884 0.0264
-5.500 -0.1592 0.00971 0.00331 -0.0920 0.6835 0.0280
-5.250 -0.1312 0.00957 0.00313 -0.0921 0.6786 0.0296
-5.000 -0.1032 0.00939 0.00295 -0.0923 0.6742 0.0320
-4.750 -0.0750 0.00925 0.00279 -0.0924 0.6695 0.0341
-4.500 -0.0468 0.00911 0.00263 -0.0925 0.6649 0.0364
-4.250 -0.0188 0.00898 0.00249 -0.0927 0.6608 0.0396
-4.000 0.0097 0.00886 0.00236 -0.0929 0.6564 0.0430
-3.750 0.0379 0.00873 0.00224 -0.0930 0.6515 0.0475
-3.500 0.0662 0.00863 0.00212 -0.0932 0.6471 0.0521
-3.250 0.0946 0.00851 0.00202 -0.0934 0.6432 0.0579
-3.000 0.1230 0.00840 0.00192 -0.0936 0.6385 0.0651
-2.750 0.1514 0.00832 0.00184 -0.0937 0.6337 0.0720
-2.500 0.1797 0.00822 0.00176 -0.0939 0.6295 0.0821
-2.250 0.2082 0.00812 0.00169 -0.0941 0.6252 0.0941
-2.000 0.2366 0.00803 0.00163 -0.0943 0.6204 0.1070
-1.750 0.2648 0.00795 0.00157 -0.0945 0.6156 0.1236
-1.500 0.2933 0.00785 0.00152 -0.0947 0.6115 0.1432
-1.250 0.3216 0.00773 0.00148 -0.0950 0.6066 0.1702
-1.000 0.3497 0.00763 0.00145 -0.0952 0.6014 0.2036
-0.750 0.3779 0.00750 0.00143 -0.0954 0.5968 0.2424
-0.500 0.4060 0.00733 0.00140 -0.0956 0.5915 0.2954
-0.250 0.4337 0.00714 0.00139 -0.0959 0.5863 0.3659
0.000 0.4614 0.00691 0.00139 -0.0961 0.5819 0.4495
0.250 0.4892 0.00668 0.00140 -0.0963 0.5773 0.5363
0.500 0.5169 0.00653 0.00143 -0.0965 0.5722 0.6071
0.750 0.5447 0.00646 0.00148 -0.0966 0.5673 0.6572
1.000 0.5729 0.00642 0.00153 -0.0967 0.5624 0.6958
1.250 0.6008 0.00641 0.00158 -0.0968 0.5574 0.7259
1.500 0.6286 0.00644 0.00165 -0.0969 0.5527 0.7517
1.750 0.6566 0.00645 0.00171 -0.0969 0.5479 0.7733
2.000 0.6840 0.00647 0.00179 -0.0969 0.5423 0.8016
2.250 0.7107 0.00651 0.00189 -0.0967 0.5370 0.8271
2.500 0.7384 0.00656 0.00196 -0.0967 0.5313 0.8404
3.000 0.7931 0.00671 0.00211 -0.0967 0.5192 0.8580
3.250 0.8207 0.00679 0.00219 -0.0967 0.5129 0.8662
3.500 0.8472 0.00689 0.00229 -0.0965 0.5069 0.8745
3.750 0.8747 0.00696 0.00237 -0.0966 0.5016 0.8825
4.000 0.9011 0.00705 0.00248 -0.0964 0.4949 0.8906
4.250 0.9274 0.00716 0.00258 -0.0962 0.4872 0.8990
4.500 0.9526 0.00728 0.00270 -0.0958 0.4780 0.9081
4.750 0.9781 0.00738 0.00282 -0.0954 0.4701 0.9174
5.000 1.0026 0.00752 0.00295 -0.0949 0.4619 0.9282
5.250 1.0269 0.00761 0.00307 -0.0942 0.4545 0.9402
5.500 1.0502 0.00776 0.00322 -0.0935 0.4456 0.9550
5.750 1.0778 0.00790 0.00336 -0.0936 0.4356 0.9724
6.000 1.1071 0.00821 0.00358 -0.0944 0.4144 1.0000
6.250 1.1273 0.00866 0.00387 -0.0934 0.3821 1.0000
6.500 1.1462 0.00917 0.00421 -0.0921 0.3501 1.0000
6.750 1.1631 0.00973 0.00460 -0.0906 0.3156 1.0000
7.000 1.1795 0.01028 0.00500 -0.0889 0.2865 1.0000
7.250 1.1948 0.01083 0.00542 -0.0871 0.2611 1.0000
7.500 1.2039 0.01145 0.00589 -0.0840 0.2326 1.0000
7.750 1.2115 0.01213 0.00644 -0.0809 0.2064 1.0000
8.000 1.2209 0.01280 0.00700 -0.0782 0.1838 1.0000
8.250 1.2285 0.01360 0.00768 -0.0754 0.1598 1.0000
8.500 1.2336 0.01456 0.00850 -0.0724 0.1326 1.0000
8.750 1.2407 0.01550 0.00933 -0.0698 0.1105 1.0000
9.000 1.2487 0.01645 0.01019 -0.0675 0.0925 1.0000
9.250 1.2582 0.01737 0.01105 -0.0654 0.0786 1.0000
9.500 1.2673 0.01836 0.01198 -0.0635 0.0658 1.0000
9.750 1.2774 0.01932 0.01291 -0.0617 0.0563 1.0000
10.000 1.2881 0.02029 0.01385 -0.0601 0.0489 1.0000
10.500 1.3100 0.02228 0.01582 -0.0572 0.0379 1.0000
10.750 1.3211 0.02331 0.01686 -0.0558 0.0342 1.0000
11.000 1.3325 0.02436 0.01791 -0.0546 0.0310 1.0000
11.250 1.3430 0.02548 0.01904 -0.0533 0.0284 1.0000
11.500 1.3538 0.02662 0.02019 -0.0521 0.0258 1.0000
11.750 1.3638 0.02784 0.02143 -0.0510 0.0239 1.0000
12.000 1.3745 0.02903 0.02266 -0.0500 0.0226 1.0000
12.250 1.3850 0.03027 0.02393 -0.0490 0.0215 1.0000
12.500 1.3945 0.03163 0.02532 -0.0480 0.0203 1.0000
12.750 1.4028 0.03313 0.02684 -0.0470 0.0190 1.0000
13.000 1.4131 0.03448 0.02824 -0.0462 0.0183 1.0000
13.250 1.4225 0.03596 0.02976 -0.0454 0.0177 1.0000
13.500 1.4310 0.03755 0.03139 -0.0447 0.0168 1.0000
13.750 1.4390 0.03923 0.03311 -0.0439 0.0160 1.0000
14.000 1.4453 0.04109 0.03501 -0.0433 0.0153 1.0000
14.250 1.4543 0.04274 0.03672 -0.0427 0.0148 1.0000
14.500 1.4621 0.04456 0.03859 -0.0422 0.0144 1.0000
14.750 1.4692 0.04648 0.04056 -0.0418 0.0138 1.0000
15.000 1.4760 0.04846 0.04259 -0.0414 0.0132 1.0000
15.250 1.4812 0.05064 0.04481 -0.0411 0.0126 1.0000
15.500 1.4858 0.05296 0.04719 -0.0408 0.0122 1.0000
15.750 1.4925 0.05506 0.04935 -0.0406 0.0118 1.0000
16.000 1.4978 0.05737 0.05173 -0.0405 0.0115 1.0000
16.250 1.5029 0.05975 0.05417 -0.0405 0.0111 1.0000
16.500 1.5070 0.06227 0.05675 -0.0405 0.0107 1.0000
16.750 1.5109 0.06487 0.05941 -0.0407 0.0104 1.0000
17.000 1.5141 0.06758 0.06218 -0.0409 0.0100 1.0000
17.250 1.5155 0.07060 0.06526 -0.0412 0.0097 1.0000
17.500 1.5173 0.07362 0.06834 -0.0416 0.0094 1.0000
17.750 1.5203 0.07649 0.07130 -0.0420 0.0092 1.0000
18.000 1.5225 0.07954 0.07442 -0.0426 0.0090 1.0000
18.250 1.5236 0.08278 0.07774 -0.0432 0.0087 1.0000
18.500 1.5252 0.08600 0.08103 -0.0439 0.0086 1.0000
18.750 1.5253 0.08947 0.08458 -0.0448 0.0082 1.0000
19.000 1.5251 0.09301 0.08820 -0.0458 0.0081 1.0000
19.250 1.5244 0.09668 0.09194 -0.0468 0.0078 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 84-W-140 (fx84w140-il)