AH 79-K-132/20 (ah79k132-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-132/20 (ah79k132-il) Reynolds number: 500,000 Max Cl/Cd: 99.97 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k132-il-500000-n5.txt Download as CSV file: xf-ah79k132-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-132/20
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5475 0.03655 0.03278 -0.1031 0.7619 0.0075
-10.500 -0.5503 0.03478 0.03088 -0.1003 0.7607 0.0077
-10.250 -0.5639 0.03107 0.02679 -0.0966 0.7595 0.0077
-10.000 -0.5558 0.02946 0.02500 -0.0948 0.7584 0.0080
-9.750 -0.5489 0.02747 0.02274 -0.0927 0.7572 0.0082
-9.500 -0.5383 0.02570 0.02071 -0.0909 0.7561 0.0084
-9.250 -0.5247 0.02414 0.01890 -0.0894 0.7552 0.0086
-9.000 -0.5083 0.02282 0.01736 -0.0881 0.7543 0.0089
-8.750 -0.4908 0.02153 0.01583 -0.0869 0.7535 0.0092
-8.500 -0.4710 0.02049 0.01459 -0.0859 0.7527 0.0095
-8.250 -0.4495 0.01968 0.01358 -0.0852 0.7518 0.0098
-8.000 -0.4268 0.01901 0.01276 -0.0846 0.7510 0.0101
-7.750 -0.4071 0.01779 0.01136 -0.0836 0.7499 0.0106
-7.500 -0.3853 0.01695 0.01042 -0.0829 0.7486 0.0112
-7.250 -0.3619 0.01634 0.00974 -0.0823 0.7473 0.0117
-7.000 -0.3380 0.01579 0.00911 -0.0818 0.7461 0.0122
-6.750 -0.3139 0.01527 0.00851 -0.0814 0.7448 0.0127
-6.500 -0.2892 0.01482 0.00798 -0.0810 0.7436 0.0134
-6.250 -0.2646 0.01436 0.00743 -0.0805 0.7425 0.0140
-6.000 -0.2395 0.01396 0.00694 -0.0802 0.7413 0.0147
-5.750 -0.2147 0.01352 0.00643 -0.0798 0.7403 0.0158
-5.500 -0.1893 0.01315 0.00605 -0.0795 0.7393 0.0178
-5.250 -0.1635 0.01286 0.00572 -0.0792 0.7384 0.0200
-5.000 -0.1377 0.01255 0.00536 -0.0790 0.7374 0.0227
-4.750 -0.1120 0.01230 0.00514 -0.0787 0.7359 0.0273
-4.500 -0.0859 0.01211 0.00492 -0.0785 0.7342 0.0309
-4.250 -0.0600 0.01188 0.00472 -0.0783 0.7324 0.0364
-4.000 -0.0333 0.01173 0.00453 -0.0782 0.7307 0.0408
-3.750 -0.0069 0.01151 0.00432 -0.0781 0.7291 0.0460
-3.500 0.0199 0.01133 0.00414 -0.0780 0.7276 0.0511
-3.250 0.0467 0.01115 0.00394 -0.0779 0.7262 0.0566
-3.000 0.0739 0.01099 0.00377 -0.0779 0.7249 0.0645
-2.500 0.1274 0.01069 0.00347 -0.0778 0.7216 0.0791
-2.250 0.1538 0.01054 0.00337 -0.0777 0.7193 0.0879
-2.000 0.1805 0.01038 0.00325 -0.0776 0.7171 0.1024
-1.750 0.2070 0.01017 0.00312 -0.0775 0.7150 0.1294
-1.500 0.2332 0.00991 0.00299 -0.0774 0.7130 0.1753
-1.250 0.2584 0.00951 0.00285 -0.0772 0.7112 0.2600
-1.000 0.2808 0.00885 0.00269 -0.0766 0.7094 0.4203
-0.750 0.2947 0.00783 0.00268 -0.0743 0.7062 0.7004
-0.500 0.3164 0.00769 0.00289 -0.0726 0.7031 0.7967
-0.250 0.3426 0.00773 0.00295 -0.0721 0.7003 0.8269
0.000 0.3696 0.00776 0.00295 -0.0718 0.6979 0.8444
0.250 0.3957 0.00783 0.00300 -0.0713 0.6954 0.8614
0.500 0.4196 0.00798 0.00320 -0.0702 0.6914 0.8770
0.750 0.4456 0.00802 0.00324 -0.0698 0.6877 0.8832
1.000 0.4734 0.00799 0.00317 -0.0698 0.6844 0.8868
1.250 0.5011 0.00798 0.00313 -0.0699 0.6808 0.8900
1.500 0.5273 0.00800 0.00317 -0.0696 0.6758 0.8934
1.750 0.5534 0.00799 0.00316 -0.0692 0.6714 0.8984
2.000 0.5802 0.00800 0.00315 -0.0690 0.6668 0.9030
2.250 0.6072 0.00799 0.00315 -0.0690 0.6610 0.9047
2.500 0.6342 0.00796 0.00309 -0.0689 0.6555 0.9064
2.750 0.6609 0.00798 0.00313 -0.0688 0.6481 0.9083
3.000 0.6875 0.00797 0.00311 -0.0686 0.6407 0.9102
3.250 0.7139 0.00799 0.00312 -0.0685 0.6308 0.9122
3.500 0.7398 0.00803 0.00313 -0.0682 0.6198 0.9146
3.750 0.7654 0.00810 0.00317 -0.0679 0.6084 0.9171
4.000 0.7901 0.00817 0.00321 -0.0674 0.5963 0.9188
4.250 0.8143 0.00827 0.00328 -0.0669 0.5836 0.9206
4.500 0.8375 0.00842 0.00338 -0.0661 0.5665 0.9226
4.750 0.8597 0.00860 0.00352 -0.0652 0.5474 0.9247
5.000 0.8813 0.00883 0.00367 -0.0642 0.5276 0.9267
5.250 0.9031 0.00905 0.00385 -0.0633 0.5097 0.9289
5.750 0.9424 0.00960 0.00428 -0.0607 0.4684 0.9334
6.000 0.9592 0.00994 0.00456 -0.0589 0.4442 0.9358
6.250 0.9749 0.01032 0.00486 -0.0569 0.4185 0.9386
6.500 0.9903 0.01070 0.00517 -0.0549 0.3953 0.9416
6.750 1.0061 0.01105 0.00549 -0.0530 0.3772 0.9449
7.000 1.0201 0.01140 0.00581 -0.0507 0.3598 0.9486
7.250 1.0302 0.01180 0.00616 -0.0478 0.3392 0.9534
7.500 1.0356 0.01246 0.00673 -0.0443 0.3080 0.9599
7.750 1.0441 0.01360 0.00764 -0.0425 0.2601 0.9695
8.000 1.0562 0.01525 0.00898 -0.0425 0.1995 1.0000
8.250 1.0567 0.01684 0.01030 -0.0401 0.1535 1.0000
8.500 1.0582 0.01837 0.01157 -0.0377 0.1111 1.0000
8.750 1.0577 0.02005 0.01296 -0.0351 0.0637 1.0000
9.000 1.0655 0.02126 0.01406 -0.0334 0.0454 1.0000
9.250 1.0769 0.02227 0.01504 -0.0321 0.0342 1.0000
9.500 1.0843 0.02355 0.01623 -0.0304 0.0172 1.0000
9.750 1.0939 0.02472 0.01737 -0.0290 0.0104 1.0000
10.000 1.1054 0.02578 0.01846 -0.0278 0.0078 1.0000
10.250 1.1181 0.02677 0.01950 -0.0268 0.0070 1.0000
10.500 1.1272 0.02802 0.02080 -0.0255 0.0059 1.0000
10.750 1.1384 0.02916 0.02200 -0.0244 0.0053 1.0000
11.000 1.1486 0.03037 0.02329 -0.0233 0.0049 1.0000
11.250 1.1585 0.03163 0.02462 -0.0222 0.0046 1.0000
11.500 1.1674 0.03299 0.02605 -0.0211 0.0043 1.0000
11.750 1.1759 0.03439 0.02755 -0.0200 0.0042 1.0000
12.000 1.1804 0.03618 0.02941 -0.0188 0.0038 1.0000
12.250 1.1864 0.03790 0.03121 -0.0177 0.0037 1.0000
12.500 1.1931 0.03963 0.03303 -0.0168 0.0037 1.0000
12.750 1.1951 0.04185 0.03534 -0.0158 0.0036 1.0000
13.000 1.1949 0.04438 0.03797 -0.0148 0.0035 1.0000
13.250 1.1997 0.04647 0.04015 -0.0141 0.0034 1.0000
13.500 1.2074 0.04829 0.04205 -0.0137 0.0034 1.0000
13.750 1.2078 0.05094 0.04480 -0.0131 0.0034 1.0000
14.000 1.2136 0.05307 0.04702 -0.0127 0.0032 1.0000
14.250 1.2179 0.05541 0.04945 -0.0125 0.0031 1.0000
14.500 1.2186 0.05818 0.05233 -0.0121 0.0030 1.0000
14.750 1.2188 0.06108 0.05533 -0.0119 0.0030 1.0000
15.000 1.2234 0.06356 0.05792 -0.0120 0.0029 1.0000
15.250 1.2212 0.06686 0.06134 -0.0120 0.0029 1.0000
15.500 1.2217 0.06991 0.06450 -0.0122 0.0028 1.0000
15.750 1.2218 0.07307 0.06776 -0.0124 0.0028 1.0000
16.000 1.2202 0.07651 0.07133 -0.0128 0.0027 1.0000
16.250 1.2193 0.07994 0.07486 -0.0133 0.0027 1.0000
16.500 1.2178 0.08352 0.07856 -0.0140 0.0027 1.0000
16.750 1.2154 0.08731 0.08246 -0.0149 0.0026 1.0000
17.000 1.2125 0.09124 0.08651 -0.0158 0.0026 1.0000
17.250 1.2084 0.09540 0.09081 -0.0169 0.0026 1.0000
17.500 1.2045 0.09968 0.09521 -0.0183 0.0025 1.0000
17.750 1.1997 0.10418 0.09983 -0.0198 0.0025 1.0000
18.000 1.1950 0.10875 0.10453 -0.0216 0.0024 1.0000
18.250 1.1894 0.11359 0.10949 -0.0236 0.0024 1.0000
18.500 1.1806 0.11900 0.11507 -0.0257 0.0025 1.0000
18.750 1.1754 0.12400 0.12018 -0.0281 0.0024 1.0000
19.000 1.1682 0.12942 0.12573 -0.0307 0.0024 1.0000
19.250 1.1601 0.13510 0.13156 -0.0336 0.0024 1.0000
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Polar data table (+)
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