AH 80-136 (ah80136-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-136 (ah80136-il) Reynolds number: 500,000 Max Cl/Cd: 105.42 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80136-il-500000-n5.txt Download as CSV file: xf-ah80136-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-136
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6234 0.06846 0.06527 0.0048 0.5934 0.0077
-7.750 -0.7022 0.03104 0.02607 0.0022 0.5934 0.0076
-7.500 -0.6897 0.02628 0.02068 0.0036 0.5919 0.0079
-7.250 -0.6696 0.02370 0.01769 0.0044 0.5903 0.0082
-7.000 -0.6471 0.02180 0.01545 0.0050 0.5888 0.0085
-6.750 -0.6230 0.02030 0.01367 0.0055 0.5872 0.0088
-6.500 -0.5980 0.01912 0.01225 0.0058 0.5856 0.0091
-6.250 -0.5723 0.01817 0.01109 0.0061 0.5839 0.0094
-6.000 -0.5465 0.01721 0.00999 0.0064 0.5822 0.0097
-5.750 -0.5202 0.01648 0.00918 0.0066 0.5805 0.0102
-5.500 -0.4928 0.01610 0.00876 0.0065 0.5789 0.0107
-5.250 -0.4654 0.01569 0.00828 0.0065 0.5772 0.0114
-5.000 -0.4382 0.01516 0.00767 0.0066 0.5756 0.0121
-4.750 -0.4110 0.01461 0.00701 0.0068 0.5740 0.0127
-4.500 -0.3840 0.01405 0.00635 0.0069 0.5723 0.0134
-4.250 -0.3565 0.01364 0.00589 0.0069 0.5708 0.0144
-4.000 -0.3286 0.01334 0.00555 0.0068 0.5692 0.0156
-3.750 -0.3005 0.01302 0.00519 0.0068 0.5678 0.0169
-3.500 -0.2724 0.01270 0.00482 0.0067 0.5662 0.0183
-3.250 -0.2441 0.01244 0.00458 0.0066 0.5645 0.0204
-3.000 -0.2156 0.01223 0.00434 0.0064 0.5627 0.0225
-2.750 -0.1871 0.01199 0.00406 0.0063 0.5609 0.0244
-2.500 -0.1588 0.01172 0.00378 0.0061 0.5593 0.0275
-2.250 -0.1302 0.01153 0.00355 0.0060 0.5579 0.0303
-2.000 -0.1015 0.01137 0.00334 0.0058 0.5565 0.0327
-1.750 -0.0729 0.01117 0.00312 0.0056 0.5550 0.0381
-1.500 -0.0439 0.01102 0.00296 0.0053 0.5533 0.0424
-1.250 -0.0150 0.01083 0.00280 0.0051 0.5515 0.0529
-1.000 0.0133 0.01051 0.00265 0.0048 0.5498 0.1002
-0.750 0.0406 0.00997 0.00250 0.0046 0.5481 0.2171
-0.500 0.0657 0.00902 0.00234 0.0045 0.5464 0.4430
-0.250 0.0921 0.00853 0.00228 0.0045 0.5447 0.5754
0.000 0.1181 0.00809 0.00222 0.0048 0.5431 0.6786
0.250 0.1396 0.00757 0.00227 0.0065 0.5417 0.8407
0.500 0.1645 0.00750 0.00241 0.0079 0.5401 0.9279
0.750 0.1985 0.00756 0.00248 0.0069 0.5381 0.9592
1.000 0.2319 0.00761 0.00249 0.0058 0.5360 0.9670
1.250 0.2652 0.00765 0.00250 0.0046 0.5339 0.9728
1.500 0.2982 0.00769 0.00249 0.0034 0.5318 0.9776
1.750 0.3330 0.00772 0.00249 0.0019 0.5297 0.9810
2.000 0.3670 0.00777 0.00247 0.0005 0.5275 0.9846
2.250 0.4011 0.00780 0.00250 -0.0010 0.5245 0.9879
2.500 0.4358 0.00783 0.00252 -0.0026 0.5211 0.9908
2.750 0.4695 0.00786 0.00254 -0.0040 0.5181 0.9939
3.000 0.5045 0.00789 0.00256 -0.0057 0.5154 0.9963
3.250 0.5403 0.00794 0.00257 -0.0075 0.5130 0.9988
3.500 0.5715 0.00798 0.00263 -0.0084 0.5103 1.0000
3.750 0.5988 0.00802 0.00270 -0.0085 0.5073 1.0000
4.000 0.6260 0.00807 0.00276 -0.0086 0.5042 1.0000
4.250 0.6532 0.00812 0.00280 -0.0086 0.5012 1.0000
4.500 0.6804 0.00818 0.00285 -0.0087 0.4985 1.0000
4.750 0.7079 0.00824 0.00298 -0.0088 0.4949 1.0000
5.000 0.7354 0.00831 0.00308 -0.0089 0.4911 1.0000
5.250 0.7628 0.00838 0.00316 -0.0091 0.4874 1.0000
5.500 0.7903 0.00846 0.00325 -0.0092 0.4837 1.0000
5.750 0.8180 0.00854 0.00340 -0.0094 0.4790 1.0000
6.000 0.8456 0.00863 0.00351 -0.0096 0.4734 1.0000
6.250 0.8733 0.00873 0.00364 -0.0098 0.4671 1.0000
6.500 0.9011 0.00884 0.00380 -0.0101 0.4599 1.0000
6.750 0.9289 0.00896 0.00395 -0.0104 0.4524 1.0000
7.000 0.9567 0.00912 0.00412 -0.0108 0.4401 1.0000
7.250 0.9846 0.00934 0.00433 -0.0112 0.4233 1.0000
7.500 1.0121 0.00969 0.00462 -0.0118 0.3999 1.0000
7.750 1.0393 0.01019 0.00503 -0.0125 0.3721 1.0000
8.000 1.0659 0.01088 0.00560 -0.0133 0.3386 1.0000
8.250 1.0913 0.01181 0.00637 -0.0144 0.3013 1.0000
8.500 1.1145 0.01312 0.00744 -0.0157 0.2508 1.0000
8.750 1.1340 0.01494 0.00894 -0.0173 0.1900 1.0000
9.000 1.1507 0.01714 0.01088 -0.0195 0.1374 1.0000
9.250 1.1621 0.02027 0.01376 -0.0230 0.0904 1.0000
9.500 1.1672 0.02271 0.01607 -0.0238 0.0657 1.0000
9.750 1.1726 0.02465 0.01796 -0.0236 0.0526 1.0000
10.000 1.1796 0.02646 0.01976 -0.0233 0.0433 1.0000
10.250 1.1867 0.02824 0.02154 -0.0231 0.0361 1.0000
10.500 1.1943 0.02998 0.02327 -0.0228 0.0300 1.0000
10.750 1.2016 0.03173 0.02504 -0.0225 0.0249 1.0000
11.000 1.2073 0.03362 0.02692 -0.0222 0.0201 1.0000
11.250 1.2132 0.03548 0.02880 -0.0218 0.0164 1.0000
11.500 1.2191 0.03737 0.03071 -0.0215 0.0138 1.0000
11.750 1.2246 0.03929 0.03267 -0.0211 0.0120 1.0000
12.000 1.2293 0.04130 0.03472 -0.0208 0.0106 1.0000
12.250 1.2359 0.04323 0.03673 -0.0206 0.0096 1.0000
12.500 1.2411 0.04534 0.03889 -0.0204 0.0088 1.0000
12.750 1.2451 0.04760 0.04120 -0.0202 0.0080 1.0000
13.000 1.2492 0.04992 0.04359 -0.0201 0.0075 1.0000
13.250 1.2542 0.05217 0.04592 -0.0201 0.0071 1.0000
13.500 1.2586 0.05452 0.04835 -0.0201 0.0068 1.0000
13.750 1.2624 0.05698 0.05088 -0.0201 0.0064 1.0000
14.000 1.2656 0.05951 0.05349 -0.0202 0.0061 1.0000
14.250 1.2673 0.06228 0.05632 -0.0204 0.0058 1.0000
14.500 1.2676 0.06525 0.05937 -0.0206 0.0055 1.0000
14.750 1.2667 0.06843 0.06264 -0.0208 0.0052 1.0000
15.000 1.2691 0.07122 0.06552 -0.0211 0.0051 1.0000
15.250 1.2705 0.07420 0.06859 -0.0215 0.0049 1.0000
15.500 1.2714 0.07729 0.07177 -0.0220 0.0047 1.0000
15.750 1.2718 0.08047 0.07504 -0.0225 0.0046 1.0000
16.000 1.2708 0.08386 0.07852 -0.0231 0.0044 1.0000
16.250 1.2700 0.08730 0.08205 -0.0237 0.0043 1.0000
16.500 1.2686 0.09084 0.08569 -0.0245 0.0042 1.0000
16.750 1.2666 0.09456 0.08949 -0.0254 0.0041 1.0000
17.000 1.2643 0.09831 0.09333 -0.0263 0.0040 1.0000
17.250 1.2618 0.10214 0.09726 -0.0273 0.0039 1.0000
17.500 1.2585 0.10619 0.10140 -0.0285 0.0039 1.0000
17.750 1.2548 0.11033 0.10563 -0.0297 0.0038 1.0000
18.000 1.2508 0.11456 0.10995 -0.0311 0.0037 1.0000
18.250 1.2459 0.11896 0.11445 -0.0326 0.0037 1.0000
18.500 1.2404 0.12355 0.11913 -0.0342 0.0036 1.0000
18.750 1.2348 0.12820 0.12388 -0.0360 0.0035 1.0000
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Polar data table (+)
Polar graphs
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