SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7043 (9.1%) (sd7043-il) Reynolds number: 500,000 Max Cl/Cd: 110.14 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7043-il-500000.txt Download as CSV file: xf-sd7043-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SD7043 (9.1%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3517 0.08534 0.08317 -0.0400 1.0000 0.0195
-8.250 -0.3652 0.08346 0.08136 -0.0375 1.0000 0.0195
-8.000 -0.3740 0.07966 0.07760 -0.0376 0.9982 0.0198
-7.750 -0.3560 0.07619 0.07412 -0.0418 0.9944 0.0202
-7.500 -0.3380 0.07238 0.07032 -0.0470 0.9890 0.0206
-7.250 -0.3130 0.06700 0.06492 -0.0562 0.9850 0.0210
-7.000 -0.2872 0.06080 0.05870 -0.0674 0.9797 0.0218
-6.750 -0.2544 0.05163 0.04942 -0.0833 0.9745 0.0228
-6.500 -0.2229 0.03887 0.03591 -0.0989 0.9648 0.0248
-6.250 -0.2060 0.03229 0.02914 -0.1030 0.9586 0.0259
-6.000 -0.1908 0.02311 0.01903 -0.1042 0.9487 0.0186
-5.750 -0.1674 0.01965 0.01506 -0.1045 0.9433 0.0183
-5.500 -0.1438 0.01757 0.01260 -0.1039 0.9366 0.0185
-5.250 -0.1173 0.01697 0.01170 -0.1034 0.9311 0.0194
-5.000 -0.0933 0.01464 0.00912 -0.1030 0.9260 0.0204
-4.750 -0.0678 0.01369 0.00808 -0.1025 0.9198 0.0212
-4.500 -0.0417 0.01296 0.00726 -0.1020 0.9147 0.0223
-4.250 -0.0154 0.01230 0.00650 -0.1015 0.9090 0.0236
-4.000 0.0115 0.01197 0.00606 -0.1010 0.9029 0.0248
-3.750 0.0371 0.01093 0.00500 -0.1006 0.8979 0.0274
-3.500 0.0641 0.01050 0.00453 -0.1003 0.8913 0.0294
-3.250 0.0912 0.01013 0.00409 -0.0999 0.8855 0.0312
-3.000 0.1183 0.00960 0.00353 -0.0997 0.8796 0.0348
-2.750 0.1458 0.00931 0.00320 -0.0994 0.8728 0.0383
-2.500 0.1734 0.00898 0.00283 -0.0991 0.8672 0.0445
-2.250 0.2011 0.00857 0.00253 -0.0990 0.8596 0.0746
-2.000 0.2284 0.00804 0.00232 -0.0989 0.8532 0.1737
-1.750 0.2558 0.00765 0.00222 -0.0990 0.8454 0.2649
-1.500 0.2831 0.00732 0.00212 -0.0989 0.8383 0.3581
-1.250 0.3105 0.00701 0.00208 -0.0988 0.8298 0.4532
-1.000 0.3375 0.00673 0.00203 -0.0985 0.8221 0.5483
-0.750 0.3640 0.00646 0.00204 -0.0980 0.8123 0.6433
-0.500 0.3900 0.00626 0.00203 -0.0973 0.8033 0.7224
-0.250 0.4153 0.00611 0.00202 -0.0964 0.7935 0.7877
0.000 0.4387 0.00595 0.00201 -0.0950 0.7826 0.8556
0.250 0.4610 0.00577 0.00193 -0.0932 0.7717 0.9282
0.500 0.4958 0.00572 0.00182 -0.0944 0.7596 1.0000
0.750 0.5238 0.00578 0.00179 -0.0943 0.7465 1.0000
1.000 0.5517 0.00585 0.00177 -0.0942 0.7322 1.0000
1.250 0.5795 0.00593 0.00176 -0.0940 0.7169 1.0000
1.500 0.6071 0.00602 0.00177 -0.0938 0.7005 1.0000
1.750 0.6346 0.00613 0.00180 -0.0936 0.6825 1.0000
2.000 0.6619 0.00626 0.00183 -0.0934 0.6632 1.0000
2.250 0.6889 0.00642 0.00188 -0.0931 0.6429 1.0000
2.500 0.7159 0.00658 0.00195 -0.0928 0.6203 1.0000
2.750 0.7424 0.00678 0.00203 -0.0925 0.5967 1.0000
3.000 0.7689 0.00699 0.00213 -0.0922 0.5713 1.0000
3.250 0.7952 0.00722 0.00226 -0.0918 0.5449 1.0000
3.500 0.8212 0.00748 0.00240 -0.0915 0.5171 1.0000
3.750 0.8469 0.00777 0.00255 -0.0911 0.4875 1.0000
4.000 0.8723 0.00808 0.00273 -0.0906 0.4565 1.0000
4.250 0.8977 0.00841 0.00293 -0.0902 0.4256 1.0000
4.500 0.9227 0.00877 0.00315 -0.0898 0.3939 1.0000
4.750 0.9476 0.00916 0.00339 -0.0893 0.3622 1.0000
5.000 0.9723 0.00955 0.00366 -0.0889 0.3320 1.0000
5.250 0.9968 0.00997 0.00393 -0.0884 0.3024 1.0000
5.500 1.0213 0.01038 0.00422 -0.0879 0.2751 1.0000
5.750 1.0457 0.01081 0.00453 -0.0874 0.2497 1.0000
6.000 1.0698 0.01125 0.00486 -0.0869 0.2263 1.0000
6.250 1.0941 0.01167 0.00520 -0.0864 0.2054 1.0000
6.500 1.1182 0.01209 0.00554 -0.0859 0.1870 1.0000
6.750 1.1420 0.01254 0.00592 -0.0853 0.1701 1.0000
7.000 1.1655 0.01301 0.00631 -0.0848 0.1541 1.0000
7.250 1.1890 0.01346 0.00672 -0.0842 0.1400 1.0000
7.500 1.2124 0.01391 0.00713 -0.0835 0.1276 1.0000
7.750 1.2355 0.01438 0.00757 -0.0829 0.1160 1.0000
8.000 1.2582 0.01486 0.00803 -0.0822 0.1053 1.0000
8.250 1.2804 0.01538 0.00853 -0.0814 0.0960 1.0000
8.500 1.3012 0.01601 0.00911 -0.0804 0.0866 1.0000
8.750 1.3237 0.01645 0.00960 -0.0797 0.0796 1.0000
9.000 1.3439 0.01710 0.01023 -0.0787 0.0728 1.0000
9.250 1.3648 0.01764 0.01080 -0.0777 0.0673 1.0000
9.500 1.3829 0.01840 0.01156 -0.0764 0.0618 1.0000
9.750 1.4035 0.01891 0.01214 -0.0754 0.0579 1.0000
10.000 1.4204 0.01969 0.01291 -0.0739 0.0539 1.0000
10.250 1.4364 0.02048 0.01377 -0.0723 0.0508 1.0000
10.500 1.4541 0.02104 0.01441 -0.0709 0.0482 1.0000
10.750 1.4681 0.02174 0.01514 -0.0689 0.0457 1.0000
11.000 1.4750 0.02288 0.01633 -0.0660 0.0430 1.0000
11.250 1.4867 0.02374 0.01728 -0.0639 0.0414 1.0000
11.500 1.5005 0.02446 0.01809 -0.0622 0.0396 1.0000
11.750 1.5127 0.02531 0.01901 -0.0604 0.0379 1.0000
12.000 1.5219 0.02639 0.02015 -0.0584 0.0362 1.0000
12.250 1.5233 0.02812 0.02194 -0.0557 0.0344 1.0000
12.500 1.5311 0.02943 0.02337 -0.0539 0.0332 1.0000
12.750 1.5430 0.03043 0.02449 -0.0525 0.0319 1.0000
13.000 1.5538 0.03154 0.02568 -0.0512 0.0304 1.0000
13.250 1.5623 0.03287 0.02706 -0.0499 0.0290 1.0000
13.500 1.5635 0.03491 0.02916 -0.0483 0.0276 1.0000
13.750 1.5631 0.03722 0.03158 -0.0468 0.0264 1.0000
14.000 1.5728 0.03864 0.03313 -0.0460 0.0255 1.0000
14.250 1.5790 0.04044 0.03504 -0.0452 0.0244 1.0000
14.500 1.5844 0.04240 0.03709 -0.0445 0.0234 1.0000
14.750 1.5868 0.04475 0.03953 -0.0440 0.0225 1.0000
15.000 1.5824 0.04799 0.04287 -0.0437 0.0217 1.0000
15.250 1.5701 0.05235 0.04734 -0.0436 0.0209 1.0000
15.500 1.5747 0.05484 0.04999 -0.0439 0.0203 1.0000
15.750 1.5757 0.05791 0.05320 -0.0443 0.0195 1.0000
16.000 1.5749 0.06134 0.05675 -0.0451 0.0187 1.0000
16.250 1.5727 0.06513 0.06066 -0.0462 0.0180 1.0000
16.500 1.5670 0.06961 0.06524 -0.0477 0.0175 1.0000
16.750 1.5565 0.07503 0.07078 -0.0498 0.0170 1.0000
17.000 1.5419 0.08136 0.07723 -0.0524 0.0166 1.0000
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Polar data table (+)
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