FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 500,000 Max Cl/Cd: 64.21 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63143-il-500000-n5.txt Download as CSV file: xf-fx63143-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-143 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2278 0.08199 0.07915 -0.0683 0.7922 0.0094
-10.750 -0.2315 0.07750 0.07458 -0.0696 0.7693 0.0093
-10.500 -0.3364 0.07905 0.07665 -0.0677 0.9023 0.0096
-10.250 -0.3100 0.07026 0.06758 -0.0824 0.8465 0.0094
-10.000 -0.3379 0.05844 0.05556 -0.0929 0.8189 0.0094
-9.750 -0.3588 0.05382 0.05069 -0.0944 0.7867 0.0094
-9.500 -0.3779 0.05041 0.04706 -0.0933 0.7612 0.0093
-9.250 -0.4496 0.03984 0.03599 -0.0860 0.7542 0.0081
-9.000 -0.4552 0.03755 0.03346 -0.0829 0.7370 0.0080
-8.750 -0.4577 0.03513 0.03077 -0.0798 0.7206 0.0078
-8.500 -0.4846 0.02668 0.02130 -0.0728 0.7099 0.0067
-8.250 -0.4721 0.02513 0.01950 -0.0709 0.6946 0.0066
-8.000 -0.4595 0.02324 0.01730 -0.0689 0.6814 0.0064
-7.750 -0.4436 0.02166 0.01540 -0.0672 0.6677 0.0063
-7.500 -0.4258 0.02025 0.01369 -0.0657 0.6536 0.0061
-7.250 -0.4061 0.01911 0.01229 -0.0644 0.6397 0.0060
-7.000 -0.3851 0.01820 0.01118 -0.0633 0.6279 0.0059
-6.750 -0.3631 0.01750 0.01030 -0.0624 0.6176 0.0058
-6.500 -0.3411 0.01688 0.00949 -0.0614 0.6061 0.0057
-6.250 -0.3183 0.01632 0.00881 -0.0606 0.5963 0.0056
-6.000 -0.2953 0.01581 0.00818 -0.0598 0.5869 0.0056
-5.750 -0.2722 0.01539 0.00765 -0.0591 0.5729 0.0055
-5.500 -0.2491 0.01495 0.00711 -0.0583 0.5613 0.0055
-5.250 -0.2257 0.01458 0.00665 -0.0576 0.5513 0.0054
-5.000 -0.2023 0.01421 0.00619 -0.0569 0.5435 0.0054
-4.750 -0.1782 0.01386 0.00579 -0.0563 0.5368 0.0054
-4.500 -0.1539 0.01351 0.00538 -0.0558 0.5311 0.0054
-4.250 -0.1297 0.01321 0.00501 -0.0552 0.5238 0.0054
-4.000 -0.1048 0.01291 0.00466 -0.0547 0.5144 0.0054
-3.750 -0.0799 0.01267 0.00436 -0.0543 0.5067 0.0055
-3.500 -0.0544 0.01242 0.00406 -0.0539 0.4996 0.0055
-3.250 -0.0292 0.01223 0.00378 -0.0535 0.4904 0.0056
-3.000 -0.0037 0.01208 0.00356 -0.0532 0.4778 0.0057
-2.750 0.0219 0.01195 0.00335 -0.0528 0.4653 0.0058
-2.500 0.0474 0.01186 0.00316 -0.0525 0.4471 0.0060
-2.250 0.0727 0.01183 0.00301 -0.0521 0.4254 0.0063
-2.000 0.0984 0.01179 0.00287 -0.0518 0.4105 0.0066
-1.750 0.1244 0.01176 0.00278 -0.0516 0.3967 0.0071
-1.500 0.1500 0.01182 0.00275 -0.0513 0.3710 0.0126
-1.250 0.1752 0.01195 0.00276 -0.0509 0.3480 0.0136
-1.000 0.2010 0.01198 0.00271 -0.0507 0.3321 0.0138
-0.750 0.2244 0.01223 0.00275 -0.0501 0.2866 0.0141
-0.500 0.2502 0.01229 0.00275 -0.0499 0.2723 0.0149
-0.250 0.2729 0.01262 0.00287 -0.0492 0.2213 0.0153
0.000 0.2985 0.01272 0.00289 -0.0489 0.1944 0.0155
0.250 0.3233 0.01289 0.00296 -0.0486 0.1770 0.0159
0.500 0.3496 0.01292 0.00295 -0.0484 0.1695 0.0164
0.750 0.3758 0.01297 0.00297 -0.0483 0.1631 0.0183
1.000 0.4018 0.01301 0.00296 -0.0481 0.1407 0.0211
1.500 0.4536 0.01321 0.00309 -0.0478 0.1299 0.0328
1.750 0.4801 0.01329 0.00316 -0.0477 0.1262 0.0336
2.000 0.5066 0.01337 0.00325 -0.0476 0.1226 0.0346
2.250 0.5327 0.01348 0.00335 -0.0475 0.1177 0.0358
2.500 0.5591 0.01357 0.00344 -0.0474 0.1143 0.0370
2.750 0.5846 0.01372 0.00357 -0.0472 0.0964 0.0386
3.000 0.6105 0.01384 0.00369 -0.0471 0.0949 0.0416
3.250 0.6363 0.01396 0.00383 -0.0469 0.0933 0.0619
3.500 0.6620 0.01409 0.00396 -0.0467 0.0914 0.0686
3.750 0.6878 0.01419 0.00411 -0.0466 0.0898 0.0987
4.000 0.7138 0.01425 0.00427 -0.0466 0.0886 0.1506
4.250 0.7433 0.01355 0.00444 -0.0481 0.0877 0.4923
4.500 0.7708 0.01286 0.00480 -0.0486 0.0871 0.8038
4.750 0.7887 0.01303 0.00513 -0.0465 0.0868 0.8469
5.000 0.8113 0.01324 0.00539 -0.0455 0.0864 0.8631
5.250 0.8346 0.01345 0.00564 -0.0448 0.0860 0.8745
5.500 0.8568 0.01368 0.00591 -0.0438 0.0857 0.8861
5.750 0.8778 0.01394 0.00621 -0.0425 0.0849 0.8981
6.000 0.8984 0.01421 0.00652 -0.0412 0.0816 0.9051
6.250 0.9222 0.01452 0.00684 -0.0409 0.0779 0.9088
6.500 0.9452 0.01472 0.00708 -0.0402 0.0756 0.9116
6.750 0.9633 0.01509 0.00744 -0.0387 0.0616 0.9142
7.000 0.9807 0.01545 0.00779 -0.0370 0.0600 0.9182
7.250 0.9987 0.01584 0.00819 -0.0355 0.0582 0.9239
7.500 1.0128 0.01614 0.00854 -0.0331 0.0572 0.9298
7.750 1.0236 0.01642 0.00886 -0.0300 0.0562 0.9357
8.000 1.0390 0.01677 0.00926 -0.0281 0.0549 0.9404
8.250 1.0527 0.01710 0.00965 -0.0259 0.0540 0.9440
8.500 1.0620 0.01741 0.01004 -0.0228 0.0531 0.9492
8.750 1.0736 0.01779 0.01049 -0.0203 0.0524 0.9555
9.000 1.0846 0.01819 0.01097 -0.0178 0.0515 0.9595
9.250 1.0934 0.01864 0.01149 -0.0151 0.0508 0.9649
9.500 1.1048 0.01925 0.01218 -0.0132 0.0495 0.9688
9.750 1.1125 0.02005 0.01306 -0.0111 0.0477 0.9732
10.000 1.1221 0.02083 0.01391 -0.0093 0.0463 0.9789
10.250 1.1429 0.02124 0.01441 -0.0092 0.0439 0.9822
10.500 1.1611 0.02201 0.01521 -0.0092 0.0325 0.9870
11.000 1.1814 0.02483 0.01804 -0.0087 0.0225 1.0000
11.250 1.1911 0.02639 0.01966 -0.0085 0.0198 1.0000
11.500 1.1983 0.02823 0.02154 -0.0083 0.0174 1.0000
11.750 1.2063 0.03005 0.02343 -0.0083 0.0163 1.0000
12.000 1.2149 0.03186 0.02531 -0.0084 0.0158 1.0000
12.250 1.2226 0.03377 0.02731 -0.0085 0.0152 1.0000
12.500 1.2292 0.03582 0.02945 -0.0086 0.0149 1.0000
12.750 1.2346 0.03800 0.03171 -0.0087 0.0143 1.0000
13.000 1.2389 0.04032 0.03410 -0.0089 0.0138 1.0000
13.250 1.2436 0.04262 0.03649 -0.0091 0.0136 1.0000
13.500 1.2458 0.04522 0.03915 -0.0094 0.0129 1.0000
13.750 1.2477 0.04790 0.04192 -0.0098 0.0124 1.0000
14.000 1.2485 0.05078 0.04487 -0.0102 0.0120 1.0000
14.250 1.2487 0.05381 0.04800 -0.0108 0.0115 1.0000
14.500 1.2486 0.05696 0.05125 -0.0114 0.0112 1.0000
14.750 1.2525 0.05968 0.05406 -0.0121 0.0110 1.0000
15.000 1.2568 0.06242 0.05689 -0.0129 0.0108 1.0000
15.250 1.2602 0.06532 0.05989 -0.0138 0.0105 1.0000
15.500 1.2619 0.06849 0.06315 -0.0147 0.0104 1.0000
15.750 1.2647 0.07154 0.06631 -0.0157 0.0101 1.0000
16.000 1.2661 0.07488 0.06974 -0.0168 0.0098 1.0000
16.250 1.2680 0.07817 0.07313 -0.0179 0.0094 1.0000
16.500 1.2695 0.08156 0.07661 -0.0192 0.0090 1.0000
16.750 1.2706 0.08508 0.08022 -0.0205 0.0086 1.0000
17.000 1.2710 0.08873 0.08396 -0.0219 0.0083 1.0000
17.250 1.2702 0.09264 0.08795 -0.0235 0.0079 1.0000
17.500 1.2684 0.09674 0.09214 -0.0252 0.0076 1.0000
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