AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.95 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah82150a-il-1000000-n5.txt Download as CSV file: xf-ah82150a-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8363 0.04696 0.04426 -0.1080 0.9360 0.0051
-15.500 -0.8222 0.04055 0.03753 -0.1192 0.9167 0.0052
-15.250 -0.8189 0.03648 0.03314 -0.1240 0.8882 0.0052
-15.000 -0.8123 0.03470 0.03118 -0.1245 0.8685 0.0054
-14.750 -0.8165 0.03233 0.02860 -0.1240 0.8528 0.0054
-14.500 -0.8168 0.03046 0.02655 -0.1232 0.8407 0.0054
-14.250 -0.8110 0.02910 0.02507 -0.1224 0.8314 0.0056
-14.000 -0.8084 0.02757 0.02339 -0.1212 0.8235 0.0056
-13.750 -0.8038 0.02620 0.02188 -0.1199 0.8161 0.0057
-13.500 -0.7938 0.02525 0.02081 -0.1188 0.8099 0.0060
-13.250 -0.7862 0.02414 0.01959 -0.1174 0.8037 0.0060
-13.000 -0.7760 0.02324 0.01857 -0.1161 0.7980 0.0061
-12.750 -0.7668 0.02226 0.01747 -0.1146 0.7932 0.0062
-12.500 -0.7558 0.02143 0.01653 -0.1131 0.7885 0.0063
-12.250 -0.7438 0.02070 0.01569 -0.1116 0.7841 0.0064
-12.000 -0.7317 0.02001 0.01491 -0.1100 0.7802 0.0065
-11.750 -0.7220 0.01924 0.01404 -0.1078 0.7759 0.0065
-11.500 -0.7127 0.01848 0.01317 -0.1055 0.7717 0.0068
-11.000 -0.6797 0.01717 0.01167 -0.1031 0.7652 0.0073
-10.750 -0.6604 0.01664 0.01108 -0.1022 0.7620 0.0075
-10.500 -0.6404 0.01615 0.01052 -0.1015 0.7588 0.0077
-10.250 -0.6197 0.01571 0.01001 -0.1007 0.7557 0.0080
-10.000 -0.5983 0.01528 0.00951 -0.1001 0.7529 0.0084
-9.750 -0.5764 0.01484 0.00901 -0.0995 0.7500 0.0086
-9.500 -0.5540 0.01443 0.00854 -0.0990 0.7472 0.0090
-9.250 -0.5311 0.01405 0.00808 -0.0986 0.7445 0.0092
-9.000 -0.5086 0.01362 0.00759 -0.0980 0.7418 0.0097
-8.500 -0.4615 0.01291 0.00681 -0.0973 0.7369 0.0109
-8.250 -0.4369 0.01262 0.00649 -0.0971 0.7342 0.0118
-8.000 -0.4121 0.01234 0.00618 -0.0969 0.7316 0.0125
-7.750 -0.3871 0.01209 0.00588 -0.0967 0.7292 0.0130
-7.500 -0.3627 0.01176 0.00551 -0.0964 0.7268 0.0143
-7.250 -0.3375 0.01152 0.00525 -0.0963 0.7244 0.0153
-7.000 -0.3115 0.01128 0.00500 -0.0962 0.7222 0.0164
-6.750 -0.2855 0.01106 0.00475 -0.0962 0.7197 0.0173
-6.500 -0.2595 0.01084 0.00450 -0.0962 0.7174 0.0181
-6.250 -0.2336 0.01059 0.00423 -0.0961 0.7150 0.0198
-6.000 -0.2073 0.01041 0.00404 -0.0961 0.7126 0.0214
-5.750 -0.1808 0.01026 0.00385 -0.0962 0.7103 0.0228
-5.500 -0.1536 0.01010 0.00368 -0.0963 0.7083 0.0238
-5.250 -0.1270 0.00986 0.00343 -0.0964 0.7060 0.0259
-5.000 -0.1000 0.00968 0.00324 -0.0965 0.7036 0.0280
-4.750 -0.0729 0.00952 0.00308 -0.0966 0.7012 0.0298
-4.500 -0.0456 0.00939 0.00292 -0.0968 0.6989 0.0315
-4.250 -0.0183 0.00926 0.00275 -0.0969 0.6968 0.0336
-4.000 0.0091 0.00910 0.00260 -0.0971 0.6948 0.0372
-3.750 0.0369 0.00895 0.00246 -0.0974 0.6925 0.0409
-3.500 0.0647 0.00882 0.00234 -0.0976 0.6902 0.0461
-3.250 0.0925 0.00868 0.00222 -0.0978 0.6879 0.0533
-3.000 0.1201 0.00854 0.00210 -0.0981 0.6855 0.0654
-2.750 0.1476 0.00838 0.00199 -0.0983 0.6832 0.0859
-2.500 0.1749 0.00813 0.00188 -0.0986 0.6810 0.1271
-2.250 0.2025 0.00785 0.00177 -0.0990 0.6788 0.1824
-2.000 0.2303 0.00757 0.00168 -0.0995 0.6763 0.2418
-1.750 0.2580 0.00725 0.00158 -0.0999 0.6736 0.3141
-1.500 0.2852 0.00662 0.00140 -0.1006 0.6710 0.4643
-1.250 0.3126 0.00601 0.00133 -0.1013 0.6684 0.6406
-1.000 0.3414 0.00603 0.00144 -0.1016 0.6656 0.6866
-0.750 0.3702 0.00611 0.00154 -0.1018 0.6621 0.7058
-0.500 0.3992 0.00617 0.00155 -0.1022 0.6580 0.7125
-0.250 0.4274 0.00622 0.00159 -0.1024 0.6539 0.7172
0.000 0.4562 0.00627 0.00164 -0.1027 0.6501 0.7225
0.250 0.4852 0.00631 0.00166 -0.1031 0.6462 0.7254
0.500 0.5139 0.00634 0.00166 -0.1035 0.6425 0.7265
0.750 0.5425 0.00639 0.00166 -0.1039 0.6390 0.7274
1.000 0.5714 0.00640 0.00168 -0.1043 0.6354 0.7283
1.250 0.6000 0.00642 0.00169 -0.1046 0.6312 0.7292
1.500 0.6283 0.00645 0.00172 -0.1049 0.6269 0.7300
1.750 0.6567 0.00649 0.00175 -0.1052 0.6226 0.7308
2.000 0.6852 0.00652 0.00179 -0.1056 0.6179 0.7316
2.250 0.7132 0.00657 0.00184 -0.1058 0.6126 0.7325
2.500 0.7414 0.00662 0.00189 -0.1061 0.6078 0.7333
2.750 0.7695 0.00667 0.00194 -0.1064 0.6020 0.7344
3.250 0.8251 0.00680 0.00208 -0.1068 0.5900 0.7364
3.500 0.8522 0.00689 0.00216 -0.1069 0.5828 0.7374
3.750 0.8797 0.00697 0.00224 -0.1071 0.5745 0.7383
4.000 0.9063 0.00708 0.00234 -0.1071 0.5652 0.7392
4.250 0.9325 0.00720 0.00245 -0.1070 0.5539 0.7401
4.500 0.9577 0.00737 0.00257 -0.1067 0.5383 0.7410
4.750 0.9794 0.00769 0.00277 -0.1058 0.5065 0.7419
5.000 0.9968 0.00821 0.00308 -0.1041 0.4603 0.7429
5.250 1.0122 0.00880 0.00345 -0.1021 0.4128 0.7440
5.500 1.0249 0.00950 0.00389 -0.0996 0.3603 0.7453
5.750 1.0359 0.01022 0.00436 -0.0969 0.3089 0.7466
6.000 1.0405 0.01113 0.00494 -0.0930 0.2458 0.7480
6.250 1.0395 0.01198 0.00552 -0.0880 0.1927 0.7495
6.500 1.0410 0.01285 0.00618 -0.0837 0.1478 0.7510
6.750 1.0419 0.01381 0.00694 -0.0794 0.1043 0.7524
7.000 1.0444 0.01479 0.00774 -0.0757 0.0680 0.7539
7.500 1.0538 0.01683 0.00951 -0.0695 0.0141 0.7566
7.750 1.0686 0.01743 0.01012 -0.0680 0.0112 0.7578
8.000 1.0831 0.01806 0.01077 -0.0665 0.0096 0.7592
8.250 1.0975 0.01872 0.01148 -0.0651 0.0085 0.7606
8.500 1.1127 0.01936 0.01215 -0.0638 0.0080 0.7620
8.750 1.1275 0.02005 0.01288 -0.0625 0.0076 0.7636
9.000 1.1420 0.02076 0.01364 -0.0613 0.0072 0.7653
9.250 1.1555 0.02156 0.01447 -0.0599 0.0068 0.7671
9.500 1.1686 0.02241 0.01535 -0.0586 0.0064 0.7688
9.750 1.1795 0.02343 0.01643 -0.0571 0.0059 0.7703
10.000 1.1926 0.02432 0.01735 -0.0559 0.0057 0.7717
10.250 1.2061 0.02519 0.01828 -0.0547 0.0055 0.7734
10.500 1.2186 0.02615 0.01930 -0.0536 0.0054 0.7751
10.750 1.2303 0.02719 0.02039 -0.0523 0.0051 0.7769
11.000 1.2416 0.02827 0.02153 -0.0512 0.0050 0.7788
11.250 1.2531 0.02937 0.02268 -0.0501 0.0049 0.7808
11.500 1.2635 0.03057 0.02395 -0.0489 0.0047 0.7828
11.750 1.2736 0.03183 0.02526 -0.0478 0.0045 0.7848
12.250 1.2929 0.03451 0.02805 -0.0458 0.0042 0.7888
12.500 1.3006 0.03605 0.02966 -0.0447 0.0041 0.7912
12.750 1.3054 0.03791 0.03160 -0.0435 0.0039 0.7937
13.000 1.3084 0.04000 0.03379 -0.0423 0.0038 0.7965
13.250 1.3167 0.04166 0.03551 -0.0416 0.0037 0.7992
13.500 1.3244 0.04341 0.03734 -0.0409 0.0037 0.8019
13.750 1.3336 0.04504 0.03906 -0.0404 0.0036 0.8048
14.000 1.3377 0.04723 0.04135 -0.0397 0.0036 0.8079
14.250 1.3465 0.04900 0.04319 -0.0393 0.0035 0.8113
14.500 1.3536 0.05100 0.04526 -0.0389 0.0034 0.8146
14.750 1.3591 0.05320 0.04756 -0.0385 0.0033 0.8181
15.000 1.3653 0.05535 0.04980 -0.0383 0.0032 0.8221
15.250 1.3697 0.05778 0.05233 -0.0381 0.0031 0.8264
15.750 1.3760 0.06312 0.05787 -0.0380 0.0030 0.8361
16.000 1.3798 0.06580 0.06065 -0.0381 0.0029 0.8420
16.250 1.3813 0.06882 0.06378 -0.0383 0.0029 0.8485
16.500 1.3817 0.07205 0.06715 -0.0386 0.0028 0.8566
16.750 1.3847 0.07497 0.07019 -0.0390 0.0028 0.8678
17.000 1.3850 0.07825 0.07361 -0.0394 0.0027 0.8859
17.250 1.3837 0.08128 0.07688 -0.0395 0.0027 1.0000
17.500 1.3839 0.08484 0.08054 -0.0404 0.0026 1.0000
17.750 1.3836 0.08857 0.08436 -0.0415 0.0026 1.0000
18.000 1.3816 0.09264 0.08852 -0.0427 0.0026 1.0000
18.250 1.3807 0.09659 0.09257 -0.0440 0.0025 1.0000
18.500 1.3777 0.10095 0.09702 -0.0456 0.0025 1.0000
18.750 1.3742 0.10543 0.10161 -0.0473 0.0025 1.0000
19.000 1.3707 0.11001 0.10629 -0.0491 0.0024 1.0000
19.250 1.3664 0.11479 0.11117 -0.0512 0.0024 1.0000
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Polar data table (+)
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