FX 84-W-140 (fx84w140-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 84-W-140 (fx84w140-il) Reynolds number: 500,000 Max Cl/Cd: 113.3 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w140-il-500000-n5.txt Download as CSV file: xf-fx84w140-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5069 0.08819 0.08557 -0.0719 0.9517 0.0129
-13.750 -0.6859 0.04890 0.04571 -0.1004 0.9214 0.0121
-13.500 -0.7195 0.04006 0.03652 -0.1076 0.9007 0.0120
-13.250 -0.7361 0.03596 0.03219 -0.1094 0.8861 0.0121
-13.000 -0.7489 0.03301 0.02903 -0.1093 0.8743 0.0122
-12.750 -0.7560 0.03093 0.02675 -0.1080 0.8642 0.0123
-12.500 -0.7613 0.02925 0.02488 -0.1058 0.8547 0.0124
-12.250 -0.7614 0.02789 0.02333 -0.1034 0.8473 0.0126
-12.000 -0.7541 0.02651 0.02175 -0.1020 0.8406 0.0128
-11.500 -0.7289 0.02417 0.01905 -0.0997 0.8290 0.0131
-11.250 -0.7147 0.02303 0.01778 -0.0987 0.8231 0.0134
-11.000 -0.6969 0.02217 0.01680 -0.0979 0.8182 0.0138
-10.750 -0.6770 0.02139 0.01593 -0.0974 0.8129 0.0141
-10.500 -0.6564 0.02066 0.01507 -0.0968 0.8077 0.0144
-10.000 -0.6131 0.01926 0.01342 -0.0958 0.7981 0.0152
-9.750 -0.5906 0.01860 0.01263 -0.0954 0.7930 0.0157
-9.500 -0.5672 0.01803 0.01191 -0.0950 0.7884 0.0162
-9.250 -0.5443 0.01736 0.01116 -0.0947 0.7838 0.0168
-9.000 -0.5198 0.01687 0.01062 -0.0945 0.7789 0.0174
-8.750 -0.4951 0.01642 0.01008 -0.0942 0.7743 0.0181
-8.500 -0.4703 0.01594 0.00951 -0.0940 0.7702 0.0188
-8.250 -0.4450 0.01547 0.00894 -0.0938 0.7655 0.0195
-8.000 -0.4197 0.01500 0.00837 -0.0936 0.7608 0.0202
-7.750 -0.3943 0.01457 0.00790 -0.0934 0.7565 0.0211
-7.500 -0.3680 0.01423 0.00751 -0.0933 0.7524 0.0221
-7.250 -0.3416 0.01390 0.00710 -0.0933 0.7478 0.0233
-7.000 -0.3153 0.01355 0.00667 -0.0932 0.7432 0.0244
-6.750 -0.2891 0.01319 0.00627 -0.0930 0.7391 0.0257
-6.500 -0.2622 0.01289 0.00593 -0.0930 0.7348 0.0271
-6.250 -0.2351 0.01263 0.00560 -0.0930 0.7303 0.0286
-6.000 -0.2084 0.01232 0.00526 -0.0930 0.7260 0.0304
-5.750 -0.1813 0.01208 0.00499 -0.0930 0.7218 0.0324
-5.500 -0.1538 0.01185 0.00471 -0.0930 0.7173 0.0343
-5.250 -0.1267 0.01159 0.00441 -0.0930 0.7128 0.0364
-5.000 -0.0994 0.01139 0.00418 -0.0930 0.7086 0.0392
-4.750 -0.0716 0.01121 0.00396 -0.0931 0.7040 0.0419
-4.500 -0.0442 0.01098 0.00373 -0.0931 0.6992 0.0456
-4.250 -0.0165 0.01083 0.00353 -0.0932 0.6946 0.0494
-4.000 0.0111 0.01063 0.00334 -0.0932 0.6902 0.0541
-3.750 0.0390 0.01048 0.00317 -0.0933 0.6855 0.0593
-3.500 0.0667 0.01031 0.00301 -0.0934 0.6809 0.0663
-3.250 0.0945 0.01019 0.00285 -0.0935 0.6768 0.0737
-2.750 0.1505 0.00990 0.00261 -0.0938 0.6674 0.0954
-2.500 0.1783 0.00977 0.00250 -0.0939 0.6631 0.1097
-2.250 0.2062 0.00964 0.00241 -0.0940 0.6589 0.1276
-2.000 0.2341 0.00948 0.00233 -0.0942 0.6540 0.1507
-1.750 0.2618 0.00933 0.00225 -0.0943 0.6493 0.1800
-1.500 0.2894 0.00917 0.00218 -0.0944 0.6452 0.2191
-1.250 0.3171 0.00896 0.00213 -0.0946 0.6405 0.2689
-1.000 0.3444 0.00870 0.00207 -0.0948 0.6356 0.3396
-0.750 0.3711 0.00839 0.00203 -0.0949 0.6311 0.4369
-0.500 0.3978 0.00806 0.00203 -0.0949 0.6266 0.5442
-0.250 0.4246 0.00785 0.00207 -0.0948 0.6215 0.6260
0.000 0.4514 0.00777 0.00211 -0.0947 0.6166 0.6808
0.250 0.4787 0.00774 0.00216 -0.0945 0.6120 0.7199
0.500 0.5061 0.00773 0.00222 -0.0944 0.6067 0.7498
0.750 0.5331 0.00775 0.00227 -0.0942 0.6017 0.7739
1.000 0.5602 0.00778 0.00233 -0.0940 0.5971 0.7960
1.250 0.5873 0.00781 0.00239 -0.0938 0.5922 0.8170
1.500 0.6126 0.00784 0.00248 -0.0932 0.5872 0.8436
1.750 0.6381 0.00790 0.00256 -0.0926 0.5825 0.8651
2.000 0.6645 0.00794 0.00263 -0.0923 0.5773 0.8761
2.250 0.6911 0.00801 0.00269 -0.0921 0.5723 0.8853
2.500 0.7173 0.00808 0.00275 -0.0918 0.5676 0.8948
2.750 0.7434 0.00813 0.00283 -0.0914 0.5623 0.9037
3.250 0.7943 0.00828 0.00298 -0.0905 0.5514 0.9232
3.500 0.8199 0.00834 0.00306 -0.0901 0.5452 0.9336
3.750 0.8454 0.00843 0.00314 -0.0897 0.5393 0.9453
4.250 0.9036 0.00861 0.00334 -0.0905 0.5269 0.9696
4.500 0.9365 0.00874 0.00345 -0.0919 0.5211 0.9828
4.750 0.9693 0.00884 0.00358 -0.0932 0.5147 1.0000
5.250 1.0205 0.00916 0.00387 -0.0928 0.4986 1.0000
5.500 1.0454 0.00935 0.00404 -0.0925 0.4906 1.0000
5.750 1.0712 0.00950 0.00421 -0.0924 0.4828 1.0000
6.000 1.0957 0.00970 0.00440 -0.0920 0.4751 1.0000
6.250 1.1205 0.00989 0.00460 -0.0917 0.4658 1.0000
6.500 1.1434 0.01013 0.00482 -0.0910 0.4532 1.0000
6.750 1.1621 0.01052 0.00510 -0.0897 0.4312 1.0000
7.000 1.1796 0.01095 0.00542 -0.0881 0.4050 1.0000
7.250 1.1947 0.01145 0.00581 -0.0862 0.3789 1.0000
7.500 1.2066 0.01199 0.00623 -0.0838 0.3543 1.0000
7.750 1.2178 0.01251 0.00668 -0.0811 0.3321 1.0000
8.000 1.2263 0.01318 0.00724 -0.0783 0.3079 1.0000
8.250 1.2335 0.01398 0.00792 -0.0754 0.2811 1.0000
8.500 1.2400 0.01488 0.00869 -0.0726 0.2543 1.0000
8.750 1.2440 0.01597 0.00964 -0.0696 0.2242 1.0000
9.000 1.2482 0.01713 0.01066 -0.0669 0.1970 1.0000
9.250 1.2525 0.01836 0.01176 -0.0643 0.1710 1.0000
9.500 1.2555 0.01974 0.01300 -0.0618 0.1444 1.0000
9.750 1.2590 0.02115 0.01430 -0.0594 0.1212 1.0000
10.000 1.2623 0.02265 0.01569 -0.0573 0.0991 1.0000
10.500 1.2734 0.02552 0.01844 -0.0537 0.0712 1.0000
11.000 1.2879 0.02834 0.02123 -0.0508 0.0533 1.0000
11.250 1.2956 0.02979 0.02268 -0.0496 0.0471 1.0000
11.500 1.3028 0.03130 0.02419 -0.0483 0.0422 1.0000
11.750 1.3117 0.03272 0.02565 -0.0473 0.0386 1.0000
12.000 1.3181 0.03439 0.02732 -0.0462 0.0347 1.0000
12.250 1.3271 0.03589 0.02887 -0.0454 0.0325 1.0000
12.500 1.3343 0.03758 0.03060 -0.0445 0.0301 1.0000
12.750 1.3412 0.03936 0.03242 -0.0437 0.0282 1.0000
13.000 1.3491 0.04108 0.03420 -0.0430 0.0267 1.0000
13.250 1.3559 0.04295 0.03610 -0.0424 0.0250 1.0000
13.500 1.3612 0.04501 0.03821 -0.0418 0.0237 1.0000
13.750 1.3677 0.04701 0.04027 -0.0413 0.0227 1.0000
14.000 1.3745 0.04901 0.04235 -0.0409 0.0218 1.0000
14.250 1.3802 0.05116 0.04457 -0.0405 0.0209 1.0000
14.500 1.3848 0.05350 0.04696 -0.0402 0.0200 1.0000
14.750 1.3881 0.05602 0.04954 -0.0400 0.0192 1.0000
15.000 1.3925 0.05848 0.05207 -0.0399 0.0186 1.0000
15.250 1.3975 0.06090 0.05457 -0.0398 0.0180 1.0000
15.500 1.4022 0.06339 0.05714 -0.0399 0.0172 1.0000
15.750 1.4054 0.06612 0.05996 -0.0400 0.0167 1.0000
16.000 1.4082 0.06897 0.06288 -0.0402 0.0162 1.0000
16.250 1.4094 0.07206 0.06602 -0.0405 0.0156 1.0000
16.500 1.4090 0.07541 0.06945 -0.0410 0.0152 1.0000
16.750 1.4120 0.07836 0.07250 -0.0414 0.0148 1.0000
17.000 1.4143 0.08147 0.07570 -0.0420 0.0144 1.0000
17.250 1.4159 0.08471 0.07904 -0.0427 0.0139 1.0000
17.500 1.4173 0.08802 0.08243 -0.0434 0.0135 1.0000
17.750 1.4182 0.09143 0.08593 -0.0443 0.0131 1.0000
18.000 1.4179 0.09508 0.08966 -0.0453 0.0128 1.0000
18.250 1.4155 0.09912 0.09377 -0.0465 0.0124 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 84-W-140 (fx84w140-il)