AH 93-K-131/15 (ah93k131-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-131/15 (ah93k131-il) Reynolds number: 500,000 Max Cl/Cd: 105.45 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k131-il-500000-n5.txt Download as CSV file: xf-ah93k131-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-131/15
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4795 0.08661 0.08386 -0.0204 0.7673 0.0088
-9.250 -0.4881 0.08023 0.07753 -0.0256 0.7657 0.0089
-9.000 -0.5084 0.07160 0.06889 -0.0341 0.7639 0.0089
-8.750 -0.6769 0.02913 0.02460 -0.0335 0.7615 0.0097
-8.500 -0.6679 0.02544 0.02034 -0.0314 0.7602 0.0101
-8.250 -0.6507 0.02333 0.01783 -0.0300 0.7590 0.0104
-8.000 -0.6301 0.02187 0.01606 -0.0291 0.7578 0.0107
-7.750 -0.6093 0.02051 0.01449 -0.0282 0.7567 0.0111
-7.500 -0.5854 0.01980 0.01367 -0.0278 0.7557 0.0114
-7.250 -0.5602 0.01920 0.01298 -0.0276 0.7543 0.0118
-7.000 -0.5348 0.01857 0.01225 -0.0274 0.7527 0.0122
-6.750 -0.5095 0.01788 0.01144 -0.0272 0.7510 0.0128
-6.500 -0.4837 0.01727 0.01069 -0.0269 0.7493 0.0135
-6.250 -0.4577 0.01671 0.00999 -0.0267 0.7479 0.0141
-6.000 -0.4325 0.01598 0.00917 -0.0264 0.7465 0.0148
-5.750 -0.4065 0.01551 0.00865 -0.0262 0.7452 0.0155
-5.500 -0.3802 0.01510 0.00818 -0.0260 0.7439 0.0162
-5.250 -0.3539 0.01468 0.00767 -0.0258 0.7427 0.0170
-5.000 -0.3277 0.01426 0.00716 -0.0256 0.7416 0.0180
-4.750 -0.3005 0.01391 0.00676 -0.0256 0.7398 0.0188
-4.500 -0.2742 0.01345 0.00629 -0.0255 0.7378 0.0202
-4.250 -0.2469 0.01319 0.00601 -0.0256 0.7359 0.0214
-4.000 -0.2198 0.01290 0.00569 -0.0255 0.7341 0.0228
-3.750 -0.1929 0.01260 0.00534 -0.0254 0.7324 0.0240
-3.500 -0.1660 0.01230 0.00499 -0.0253 0.7309 0.0254
-3.250 -0.1394 0.01197 0.00465 -0.0252 0.7294 0.0276
-3.000 -0.1123 0.01173 0.00438 -0.0251 0.7280 0.0296
-2.750 -0.0848 0.01153 0.00414 -0.0251 0.7262 0.0315
-2.500 -0.0572 0.01132 0.00393 -0.0252 0.7239 0.0342
-2.250 -0.0297 0.01111 0.00374 -0.0253 0.7216 0.0381
-2.000 -0.0020 0.01095 0.00356 -0.0254 0.7195 0.0416
-1.750 0.0255 0.01075 0.00336 -0.0254 0.7174 0.0474
-1.500 0.0530 0.01057 0.00319 -0.0254 0.7156 0.0563
-1.250 0.0800 0.01035 0.00302 -0.0254 0.7139 0.0745
-1.000 0.1070 0.01012 0.00292 -0.0254 0.7117 0.1113
-0.750 0.1330 0.00977 0.00285 -0.0254 0.7089 0.1888
-0.500 0.1574 0.00930 0.00276 -0.0251 0.7062 0.3078
-0.250 0.1781 0.00858 0.00264 -0.0240 0.7036 0.4899
0.000 0.2487 0.00750 0.00304 -0.0329 0.7021 0.9126
0.250 0.2726 0.00777 0.00327 -0.0316 0.6999 0.9483
0.500 0.3181 0.00826 0.00372 -0.0350 0.6974 0.9725
0.750 0.3717 0.00840 0.00383 -0.0406 0.6943 0.9798
1.000 0.4022 0.00844 0.00384 -0.0413 0.6909 0.9836
1.250 0.4351 0.00839 0.00375 -0.0426 0.6879 0.9848
1.500 0.4680 0.00833 0.00364 -0.0439 0.6853 0.9859
1.750 0.5012 0.00832 0.00364 -0.0454 0.6814 0.9871
2.000 0.5336 0.00830 0.00362 -0.0466 0.6770 0.9884
2.250 0.5652 0.00826 0.00354 -0.0477 0.6726 0.9898
2.500 0.5965 0.00826 0.00353 -0.0487 0.6677 0.9912
2.750 0.6275 0.00826 0.00354 -0.0496 0.6619 0.9926
3.000 0.6574 0.00825 0.00349 -0.0503 0.6567 0.9938
3.250 0.6896 0.00825 0.00352 -0.0515 0.6498 0.9947
3.500 0.7216 0.00823 0.00349 -0.0527 0.6435 0.9955
3.750 0.7534 0.00825 0.00353 -0.0539 0.6358 0.9963
4.000 0.7847 0.00826 0.00352 -0.0549 0.6277 0.9972
4.250 0.8162 0.00830 0.00357 -0.0561 0.6176 0.9981
4.500 0.8475 0.00837 0.00363 -0.0572 0.6056 0.9990
4.750 0.8786 0.00846 0.00370 -0.0582 0.5911 0.9998
5.000 0.9069 0.00860 0.00380 -0.0588 0.5750 1.0000
5.250 0.9338 0.00886 0.00398 -0.0591 0.5500 1.0000
5.500 0.9602 0.00923 0.00422 -0.0594 0.5182 1.0000
5.750 0.9861 0.00962 0.00452 -0.0597 0.4910 1.0000
6.000 1.0108 0.01015 0.00491 -0.0599 0.4572 1.0000
6.250 1.0335 0.01084 0.00543 -0.0600 0.4166 1.0000
6.500 1.0537 0.01162 0.00602 -0.0597 0.3754 1.0000
6.750 1.0712 0.01248 0.00670 -0.0589 0.3357 1.0000
7.000 1.0861 0.01337 0.00742 -0.0578 0.2984 1.0000
7.250 1.0972 0.01436 0.00825 -0.0561 0.2638 1.0000
7.500 1.1037 0.01538 0.00913 -0.0536 0.2329 1.0000
7.750 1.1001 0.01640 0.01002 -0.0491 0.2051 1.0000
8.000 1.0905 0.01729 0.01079 -0.0432 0.1819 1.0000
8.250 1.0865 0.01824 0.01161 -0.0385 0.1570 1.0000
8.500 1.0857 0.01920 0.01244 -0.0345 0.1339 1.0000
8.750 1.0881 0.02010 0.01325 -0.0311 0.1134 1.0000
9.000 1.0917 0.02102 0.01408 -0.0280 0.0962 1.0000
9.250 1.0964 0.02194 0.01492 -0.0252 0.0809 1.0000
9.500 1.1023 0.02286 0.01579 -0.0225 0.0676 1.0000
9.750 1.1091 0.02377 0.01665 -0.0201 0.0561 1.0000
10.250 1.1250 0.02558 0.01842 -0.0159 0.0397 1.0000
10.500 1.1339 0.02650 0.01933 -0.0140 0.0342 1.0000
10.750 1.1422 0.02748 0.02030 -0.0121 0.0291 1.0000
11.000 1.1517 0.02842 0.02128 -0.0103 0.0249 1.0000
11.250 1.1593 0.02953 0.02239 -0.0086 0.0209 1.0000
11.500 1.1688 0.03056 0.02344 -0.0070 0.0179 1.0000
11.750 1.1769 0.03175 0.02465 -0.0055 0.0152 1.0000
12.000 1.1864 0.03291 0.02585 -0.0042 0.0134 1.0000
12.250 1.1945 0.03422 0.02718 -0.0028 0.0118 1.0000
12.500 1.2036 0.03549 0.02852 -0.0016 0.0108 1.0000
12.750 1.2125 0.03682 0.02991 -0.0005 0.0099 1.0000
13.000 1.2204 0.03828 0.03144 0.0006 0.0092 1.0000
13.250 1.2268 0.03991 0.03313 0.0017 0.0085 1.0000
13.500 1.2333 0.04156 0.03486 0.0027 0.0081 1.0000
13.750 1.2406 0.04320 0.03658 0.0036 0.0077 1.0000
14.000 1.2471 0.04496 0.03842 0.0044 0.0074 1.0000
14.250 1.2530 0.04682 0.04037 0.0052 0.0070 1.0000
14.500 1.2585 0.04874 0.04237 0.0059 0.0067 1.0000
14.750 1.2629 0.05083 0.04454 0.0065 0.0064 1.0000
15.000 1.2659 0.05312 0.04690 0.0071 0.0062 1.0000
15.250 1.2658 0.05580 0.04969 0.0076 0.0059 1.0000
15.500 1.2681 0.05828 0.05226 0.0080 0.0057 1.0000
15.750 1.2708 0.06077 0.05486 0.0082 0.0056 1.0000
16.000 1.2723 0.06346 0.05765 0.0084 0.0054 1.0000
16.250 1.2729 0.06632 0.06062 0.0084 0.0053 1.0000
16.500 1.2725 0.06936 0.06377 0.0084 0.0052 1.0000
16.750 1.2713 0.07256 0.06708 0.0082 0.0050 1.0000
17.000 1.2693 0.07592 0.07055 0.0079 0.0049 1.0000
17.250 1.2667 0.07946 0.07420 0.0074 0.0048 1.0000
17.500 1.2633 0.08318 0.07804 0.0068 0.0047 1.0000
17.750 1.2591 0.08708 0.08205 0.0060 0.0047 1.0000
18.000 1.2540 0.09116 0.08624 0.0051 0.0046 1.0000
18.250 1.2484 0.09543 0.09063 0.0039 0.0045 1.0000
18.500 1.2420 0.09991 0.09524 0.0026 0.0045 1.0000
18.750 1.2349 0.10458 0.10002 0.0011 0.0044 1.0000
19.000 1.2273 0.10939 0.10494 -0.0005 0.0044 1.0000
19.250 1.2191 0.11439 0.11006 -0.0023 0.0043 1.0000
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