FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 100,000 Max Cl/Cd: 46.45 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63143-il-100000.txt Download as CSV file: xf-fx63143-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3549 0.11533 0.11052 -0.0345 1.0000 0.0863
-10.500 -0.3631 0.11170 0.10697 -0.0376 1.0000 0.0901
-10.250 -0.3769 0.10735 0.10274 -0.0415 1.0000 0.0915
-10.000 -0.3553 0.10455 0.09993 -0.0384 1.0000 0.0942
-9.750 -0.3551 0.10128 0.09672 -0.0394 1.0000 0.0981
-9.500 -0.3894 0.09638 0.09199 -0.0469 1.0000 0.1009
-9.250 -0.3673 0.09330 0.08894 -0.0430 1.0000 0.1034
-9.000 -0.3627 0.09040 0.08607 -0.0426 1.0000 0.1069
-8.750 -0.3862 0.08577 0.08160 -0.0471 1.0000 0.1106
-8.500 -0.4267 0.08172 0.07768 -0.0497 1.0000 0.1113
-8.250 -0.4644 0.07971 0.07576 -0.0472 1.0000 0.1116
-8.000 -0.4221 0.07623 0.07242 -0.0455 1.0000 0.1172
-7.750 -0.4858 0.07630 0.07269 -0.0403 0.9970 0.1139
-7.500 -0.4723 0.07016 0.06632 -0.0495 0.9780 0.1244
-7.250 -0.4495 0.06553 0.06157 -0.0544 0.9632 0.1368
-6.500 -0.3801 0.04355 0.03736 -0.0647 0.9234 0.0652
-6.250 -0.3464 0.03731 0.03053 -0.0662 0.9141 0.0501
-6.000 -0.3125 0.03312 0.02558 -0.0671 0.9028 0.0443
-5.750 -0.2789 0.03017 0.02191 -0.0675 0.8899 0.0413
-5.500 -0.2412 0.02762 0.01897 -0.0688 0.8789 0.0410
-5.250 -0.2045 0.02570 0.01665 -0.0698 0.8675 0.0419
-5.000 -0.1743 0.02423 0.01522 -0.0702 0.8547 0.0457
-4.750 -0.1429 0.02291 0.01386 -0.0707 0.8435 0.0497
-4.500 -0.1148 0.02183 0.01278 -0.0704 0.8324 0.0557
-4.250 -0.0933 0.02108 0.01195 -0.0690 0.8203 0.0639
-4.000 -0.0717 0.02029 0.01111 -0.0678 0.8104 0.0745
-3.750 -0.0514 0.01975 0.01058 -0.0665 0.7999 0.0833
-3.500 -0.0289 0.01939 0.01014 -0.0654 0.7908 0.1009
-3.000 -0.0016 0.01700 0.00961 -0.0612 0.7743 0.4896
-2.750 0.0176 0.01674 0.01009 -0.0582 0.7662 0.6670
-2.500 0.0506 0.01722 0.01065 -0.0573 0.7591 0.7484
-2.250 0.0769 0.01771 0.01105 -0.0560 0.7502 0.7866
-2.000 0.1056 0.01822 0.01135 -0.0550 0.7435 0.8188
-1.750 0.1296 0.01902 0.01207 -0.0530 0.7344 0.8513
-1.500 0.1738 0.01985 0.01269 -0.0541 0.7283 0.8830
-1.250 0.2098 0.02031 0.01302 -0.0553 0.7207 0.8997
-1.000 0.2542 0.02055 0.01309 -0.0582 0.7141 0.9142
-0.750 0.3101 0.02075 0.01310 -0.0633 0.7083 0.9307
-0.500 0.3685 0.02084 0.01308 -0.0693 0.7006 0.9495
-0.250 0.4462 0.02053 0.01254 -0.0788 0.6941 0.9743
0.000 0.5183 0.02000 0.01192 -0.0883 0.6850 0.9958
0.250 0.5503 0.01989 0.01170 -0.0898 0.6786 1.0000
0.500 0.5680 0.02013 0.01190 -0.0886 0.6725 1.0000
0.750 0.5853 0.02035 0.01210 -0.0874 0.6654 1.0000
1.000 0.6063 0.02046 0.01212 -0.0864 0.6601 1.0000
1.250 0.6219 0.02083 0.01252 -0.0849 0.6531 1.0000
1.500 0.6406 0.02102 0.01267 -0.0837 0.6465 1.0000
1.750 0.6624 0.02112 0.01267 -0.0827 0.6411 1.0000
2.000 0.6763 0.02151 0.01314 -0.0809 0.6328 1.0000
2.250 0.6986 0.02149 0.01304 -0.0798 0.6264 1.0000
2.500 0.7135 0.02186 0.01345 -0.0780 0.6185 1.0000
2.750 0.7343 0.02187 0.01340 -0.0767 0.6111 1.0000
3.000 0.7517 0.02205 0.01357 -0.0750 0.6030 1.0000
3.250 0.7717 0.02203 0.01351 -0.0735 0.5946 1.0000
3.500 0.7896 0.02212 0.01361 -0.0718 0.5860 1.0000
3.750 0.8098 0.02207 0.01353 -0.0703 0.5777 1.0000
4.000 0.8276 0.02220 0.01367 -0.0686 0.5699 1.0000
4.250 0.8462 0.02228 0.01379 -0.0670 0.5623 1.0000
4.500 0.8710 0.02230 0.01374 -0.0664 0.5577 1.0000
4.750 0.8800 0.02290 0.01452 -0.0636 0.5500 1.0000
5.000 0.9017 0.02299 0.01462 -0.0625 0.5445 1.0000
5.250 0.9207 0.02327 0.01494 -0.0610 0.5392 1.0000
5.500 0.9313 0.02380 0.01561 -0.0584 0.5319 1.0000
5.750 0.9550 0.02383 0.01564 -0.0575 0.5267 1.0000
6.000 0.9665 0.02434 0.01627 -0.0550 0.5201 1.0000
6.250 0.9804 0.02469 0.01674 -0.0527 0.5133 1.0000
6.500 1.0080 0.02457 0.01660 -0.0524 0.5085 1.0000
6.750 1.0090 0.02536 0.01760 -0.0483 0.5005 1.0000
7.000 1.0299 0.02541 0.01771 -0.0470 0.4945 1.0000
7.250 1.0469 0.02565 0.01804 -0.0451 0.4887 1.0000
7.500 1.0521 0.02621 0.01877 -0.0416 0.4812 1.0000
7.750 1.0799 0.02602 0.01861 -0.0412 0.4757 1.0000
8.000 1.0812 0.02671 0.01950 -0.0371 0.4684 1.0000
8.250 1.0962 0.02692 0.01982 -0.0349 0.4615 1.0000
8.500 1.1238 0.02676 0.01973 -0.0346 0.4557 1.0000
8.750 1.1221 0.02755 0.02075 -0.0303 0.4471 1.0000
9.000 1.1552 0.02692 0.02014 -0.0305 0.4392 1.0000
9.250 1.1627 0.02707 0.02048 -0.0273 0.4279 1.0000
9.500 1.1782 0.02683 0.02037 -0.0251 0.4158 1.0000
9.750 1.1994 0.02640 0.02000 -0.0236 0.4033 1.0000
10.000 1.2152 0.02616 0.01984 -0.0216 0.3892 1.0000
10.250 1.2194 0.02642 0.02028 -0.0182 0.3743 1.0000
10.500 1.2239 0.02652 0.02044 -0.0148 0.3578 1.0000
10.750 1.2244 0.02706 0.02104 -0.0113 0.3393 1.0000
11.000 1.2184 0.02826 0.02239 -0.0079 0.3194 1.0000
11.250 1.2132 0.02958 0.02370 -0.0052 0.2962 1.0000
11.500 1.2047 0.03156 0.02565 -0.0029 0.2716 1.0000
11.750 1.1908 0.03437 0.02841 -0.0013 0.2421 1.0000
12.000 1.1751 0.03763 0.03145 0.0000 0.2169 1.0000
12.250 1.1577 0.04155 0.03528 0.0005 0.1874 1.0000
12.500 1.1397 0.04566 0.03916 0.0009 0.1679 1.0000
12.750 1.1252 0.04976 0.04319 0.0010 0.1452 1.0000
13.000 1.1101 0.05392 0.04712 0.0009 0.1319 1.0000
13.250 1.0999 0.05759 0.05064 0.0012 0.1170 1.0000
13.500 1.0931 0.06134 0.05441 0.0009 0.1020 1.0000
13.750 1.0910 0.06424 0.05706 0.0013 0.0916 1.0000
14.000 1.1077 0.06475 0.05732 0.0036 0.0796 1.0000
14.250 1.1247 0.06595 0.05859 0.0048 0.0729 1.0000
14.500 1.1487 0.06659 0.05919 0.0063 0.0680 1.0000
14.750 1.1719 0.06769 0.06039 0.0073 0.0644 1.0000
15.000 1.1987 0.06889 0.06159 0.0084 0.0606 1.0000
15.250 1.2102 0.07148 0.06438 0.0086 0.0577 1.0000
15.500 1.2414 0.07377 0.06669 0.0095 0.0539 1.0000
15.750 1.2266 0.07806 0.07134 0.0086 0.0528 1.0000
16.000 1.2132 0.08254 0.07613 0.0074 0.0514 1.0000
16.250 1.2357 0.08513 0.07857 0.0077 0.0464 1.0000
16.500 1.2158 0.09010 0.08387 0.0059 0.0461 1.0000
16.750 1.1941 0.09565 0.08975 0.0036 0.0457 1.0000
17.000 1.1750 0.10157 0.09597 0.0009 0.0454 1.0000
17.250 1.1546 0.10798 0.10265 -0.0023 0.0452 1.0000
17.500 1.1336 0.11493 0.10985 -0.0060 0.0452 1.0000
17.750 1.1115 0.12247 0.11763 -0.0104 0.0453 1.0000
18.000 1.0899 0.13043 0.12578 -0.0151 0.0456 1.0000
18.250 1.0693 0.13877 0.13429 -0.0203 0.0460 1.0000
18.500 1.0493 0.14752 0.14317 -0.0258 0.0463 1.0000
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