AH 81-K-144/17 (ah81k144-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 81-K-144/17 (ah81k144-il) Reynolds number: 500,000 Max Cl/Cd: 129.4 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah81k144-il-500000.txt Download as CSV file: xf-ah81k144-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 81-K-144/17
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1493 0.09128 0.08777 -0.1095 0.7645 0.0250
-11.000 -0.1473 0.08691 0.08342 -0.1121 0.7636 0.0251
-10.750 -0.1563 0.08132 0.07786 -0.1141 0.7628 0.0258
-10.500 -0.1497 0.07887 0.07541 -0.1152 0.7619 0.0263
-10.250 -0.1456 0.07565 0.07218 -0.1172 0.7609 0.0266
-10.000 -0.1383 0.07334 0.06987 -0.1186 0.7598 0.0278
-9.750 -0.1449 0.06819 0.06476 -0.1219 0.7587 0.0282
-9.500 -0.1804 0.05658 0.05322 -0.1319 0.7572 0.0270
-9.250 -0.3741 0.03377 0.02915 -0.1194 0.7543 0.0153
-9.000 -0.3773 0.03123 0.02632 -0.1159 0.7529 0.0152
-8.750 -0.3729 0.02916 0.02398 -0.1133 0.7516 0.0152
-8.500 -0.3688 0.02651 0.02099 -0.1104 0.7503 0.0153
-8.250 -0.3552 0.02496 0.01920 -0.1086 0.7491 0.0153
-8.000 -0.3428 0.02268 0.01664 -0.1067 0.7479 0.0156
-7.750 -0.3246 0.02133 0.01512 -0.1055 0.7468 0.0159
-7.500 -0.3043 0.02033 0.01397 -0.1045 0.7457 0.0161
-7.250 -0.2829 0.01979 0.01335 -0.1038 0.7447 0.0169
-7.000 -0.2616 0.01899 0.01248 -0.1028 0.7436 0.0175
-6.750 -0.2393 0.01843 0.01184 -0.1021 0.7424 0.0183
-6.500 -0.2172 0.01770 0.01100 -0.1012 0.7410 0.0190
-6.250 -0.1942 0.01715 0.01036 -0.1004 0.7395 0.0195
-6.000 -0.1753 0.01605 0.00921 -0.0991 0.7380 0.0206
-5.750 -0.1527 0.01559 0.00872 -0.0983 0.7367 0.0218
-5.500 -0.1293 0.01522 0.00831 -0.0977 0.7355 0.0234
-5.250 -0.1058 0.01483 0.00786 -0.0970 0.7344 0.0256
-5.000 -0.0829 0.01437 0.00739 -0.0962 0.7332 0.0290
-4.750 -0.0593 0.01397 0.00695 -0.0955 0.7321 0.0343
-4.500 -0.0355 0.01363 0.00660 -0.0949 0.7311 0.0440
-4.250 -0.0116 0.01338 0.00640 -0.0943 0.7300 0.0595
-4.000 0.0119 0.01320 0.00629 -0.0937 0.7288 0.0782
-3.750 0.0350 0.01297 0.00619 -0.0931 0.7272 0.1029
-3.500 0.0584 0.01276 0.00610 -0.0925 0.7254 0.1334
-3.250 0.0821 0.01255 0.00601 -0.0920 0.7237 0.1673
-3.000 0.1051 0.01228 0.00593 -0.0913 0.7223 0.2198
-2.750 0.1273 0.01194 0.00584 -0.0905 0.7209 0.2913
-2.500 0.1480 0.01150 0.00572 -0.0895 0.7195 0.3869
-2.250 0.1669 0.01101 0.00562 -0.0879 0.7182 0.5021
-2.000 0.1828 0.01051 0.00555 -0.0856 0.7170 0.6330
-1.750 0.2005 0.01026 0.00571 -0.0832 0.7159 0.7529
-1.500 0.2243 0.01043 0.00592 -0.0822 0.7147 0.8007
-1.250 0.2460 0.01058 0.00610 -0.0809 0.7125 0.8235
-1.000 0.2688 0.01074 0.00627 -0.0798 0.7104 0.8408
-0.750 0.2931 0.01083 0.00634 -0.0790 0.7084 0.8534
-0.500 0.3173 0.01090 0.00639 -0.0781 0.7067 0.8657
-0.250 0.3442 0.01092 0.00639 -0.0778 0.7051 0.8750
0.000 0.3707 0.01092 0.00636 -0.0774 0.7038 0.8837
0.250 0.3972 0.01092 0.00633 -0.0770 0.7026 0.8921
0.500 0.4249 0.01091 0.00629 -0.0769 0.7015 0.8991
0.750 0.4507 0.01098 0.00633 -0.0764 0.7002 0.9081
1.000 0.4720 0.01105 0.00647 -0.0751 0.6973 0.9174
1.250 0.4948 0.01106 0.00651 -0.0740 0.6947 0.9287
1.500 0.5188 0.01100 0.00647 -0.0731 0.6925 0.9395
1.750 0.5515 0.01093 0.00639 -0.0742 0.6908 0.9452
2.000 0.5811 0.01084 0.00628 -0.0747 0.6893 0.9503
2.250 0.6133 0.01073 0.00616 -0.0757 0.6879 0.9546
2.500 0.6499 0.01067 0.00607 -0.0777 0.6866 0.9575
2.750 0.6813 0.01072 0.00614 -0.0788 0.6843 0.9610
3.000 0.7075 0.01077 0.00626 -0.0788 0.6810 0.9654
3.250 0.7418 0.01075 0.00626 -0.0805 0.6785 0.9675
3.500 0.7780 0.01068 0.00619 -0.0826 0.6763 0.9691
3.750 0.8141 0.01057 0.00610 -0.0846 0.6745 0.9706
4.000 0.8504 0.01046 0.00597 -0.0865 0.6727 0.9720
4.250 0.8838 0.01044 0.00599 -0.0880 0.6698 0.9739
4.500 0.9142 0.01046 0.00610 -0.0890 0.6658 0.9767
4.750 0.9478 0.01036 0.00603 -0.0905 0.6625 0.9784
5.000 0.9843 0.01024 0.00593 -0.0925 0.6600 0.9794
5.250 1.0208 0.01011 0.00580 -0.0946 0.6576 0.9804
5.500 1.0516 0.01013 0.00595 -0.0957 0.6521 0.9827
5.750 1.0854 0.00984 0.00569 -0.0970 0.6461 0.9845
6.000 1.1163 0.00955 0.00544 -0.0978 0.6352 0.9877
6.250 1.1495 0.00925 0.00516 -0.0990 0.6181 0.9899
6.500 1.1803 0.00919 0.00509 -0.1000 0.5986 0.9930
6.750 1.2073 0.00933 0.00522 -0.1003 0.5765 0.9999
7.000 1.2125 0.00950 0.00534 -0.0961 0.5573 1.0000
7.250 1.2209 0.00985 0.00559 -0.0927 0.5299 1.0000
7.500 1.2255 0.01049 0.00606 -0.0888 0.4919 1.0000
7.750 1.2231 0.01142 0.00678 -0.0838 0.4514 1.0000
8.000 1.2152 0.01263 0.00778 -0.0783 0.4103 1.0000
8.250 1.2077 0.01443 0.00937 -0.0744 0.3669 1.0000
8.500 1.2008 0.01680 0.01150 -0.0716 0.3191 1.0000
8.750 1.1862 0.01963 0.01396 -0.0680 0.2559 1.0000
9.000 1.1774 0.02205 0.01606 -0.0649 0.2015 1.0000
9.250 1.1651 0.02472 0.01833 -0.0614 0.1375 1.0000
9.500 1.1566 0.02718 0.02046 -0.0584 0.0837 1.0000
9.750 1.1545 0.02927 0.02232 -0.0561 0.0512 1.0000
10.000 1.1585 0.03099 0.02396 -0.0543 0.0383 1.0000
10.250 1.1672 0.03238 0.02537 -0.0530 0.0326 1.0000
10.500 1.1722 0.03412 0.02712 -0.0514 0.0287 1.0000
10.750 1.1843 0.03534 0.02840 -0.0505 0.0271 1.0000
11.000 1.1944 0.03676 0.02988 -0.0496 0.0250 1.0000
11.250 1.2016 0.03842 0.03158 -0.0484 0.0235 1.0000
11.500 1.2015 0.04077 0.03399 -0.0467 0.0219 1.0000
11.750 1.2140 0.04208 0.03536 -0.0461 0.0208 1.0000
12.000 1.2215 0.04382 0.03717 -0.0451 0.0195 1.0000
12.250 1.2308 0.04542 0.03881 -0.0443 0.0184 1.0000
12.500 1.2330 0.04769 0.04112 -0.0431 0.0175 1.0000
12.750 1.2284 0.05060 0.04411 -0.0413 0.0167 1.0000
13.000 1.2373 0.05230 0.04590 -0.0406 0.0164 1.0000
13.250 1.2457 0.05407 0.04774 -0.0399 0.0160 1.0000
13.500 1.2535 0.05593 0.04968 -0.0392 0.0153 1.0000
13.750 1.2620 0.05775 0.05157 -0.0386 0.0146 1.0000
14.000 1.2707 0.05961 0.05346 -0.0383 0.0139 1.0000
14.250 1.2761 0.06172 0.05563 -0.0375 0.0135 1.0000
14.500 1.2811 0.06381 0.05776 -0.0366 0.0132 1.0000
14.750 1.2842 0.06572 0.05973 -0.0346 0.0126 1.0000
15.000 1.2915 0.06788 0.06202 -0.0344 0.0123 1.0000
15.250 1.2987 0.06988 0.06414 -0.0337 0.0120 1.0000
15.500 1.3052 0.07207 0.06643 -0.0334 0.0116 1.0000
15.750 1.3114 0.07418 0.06866 -0.0326 0.0114 1.0000
16.000 1.3167 0.07646 0.07105 -0.0321 0.0111 1.0000
16.250 1.3211 0.07891 0.07361 -0.0316 0.0108 1.0000
16.500 1.3236 0.08173 0.07653 -0.0319 0.0104 1.0000
16.750 1.3266 0.08442 0.07932 -0.0316 0.0103 1.0000
17.000 1.3274 0.08737 0.08241 -0.0313 0.0102 1.0000
17.250 1.3289 0.09037 0.08547 -0.0319 0.0099 1.0000
17.500 1.3280 0.09361 0.08882 -0.0317 0.0097 1.0000
17.750 1.3204 0.09761 0.09299 -0.0309 0.0093 1.0000
18.000 1.3102 0.10256 0.09816 -0.0317 0.0092 1.0000
18.250 1.3036 0.10712 0.10289 -0.0331 0.0092 1.0000
18.500 1.2915 0.11257 0.10855 -0.0344 0.0092 1.0000
18.750 1.2844 0.11766 0.11380 -0.0368 0.0090 1.0000
19.000 1.2711 0.12376 0.12012 -0.0391 0.0089 1.0000
19.250 1.2565 0.13036 0.12693 -0.0420 0.0088 1.0000
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