AH 93-W-215 (ah93w215-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-215 (ah93w215-il) Reynolds number: 100,000 Max Cl/Cd: 27.13 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w215-il-100000-n5.txt Download as CSV file: xf-ah93w215-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6902 0.08030 0.07371 -0.0792 1.0000 0.0727
-15.250 -0.7392 0.07079 0.06388 -0.0840 1.0000 0.0733
-15.000 -0.7699 0.06460 0.05741 -0.0864 1.0000 0.0740
-14.750 -0.7864 0.06040 0.05304 -0.0875 1.0000 0.0749
-14.500 -0.7789 0.05884 0.05156 -0.0873 1.0000 0.0760
-14.250 -0.7801 0.05653 0.04922 -0.0873 1.0000 0.0771
-14.000 -0.7842 0.05402 0.04664 -0.0872 1.0000 0.0783
-13.750 -0.7896 0.05152 0.04405 -0.0868 1.0000 0.0796
-13.500 -0.7969 0.04907 0.04146 -0.0861 1.0000 0.0810
-13.250 -0.7956 0.04606 0.03823 -0.0868 0.9896 0.0827
-13.000 -0.7653 0.04433 0.03658 -0.0899 0.9254 0.0848
-12.750 -0.7249 0.04209 0.03415 -0.0965 0.8937 0.0878
-12.500 -0.6824 0.03944 0.03103 -0.1041 0.8687 0.0916
-12.250 -0.6353 0.03794 0.02944 -0.1105 0.8451 0.0949
-12.000 -0.6029 0.03651 0.02774 -0.1143 0.8248 0.0984
-11.750 -0.5789 0.03513 0.02604 -0.1164 0.8089 0.1019
-11.500 -0.5549 0.03421 0.02508 -0.1176 0.7958 0.1048
-11.250 -0.5347 0.03325 0.02400 -0.1183 0.7854 0.1082
-11.000 -0.5153 0.03227 0.02280 -0.1187 0.7762 0.1120
-10.750 -0.4935 0.03144 0.02195 -0.1193 0.7687 0.1154
-10.500 -0.4755 0.03067 0.02112 -0.1192 0.7605 0.1193
-10.250 -0.4548 0.02988 0.02013 -0.1193 0.7536 0.1239
-10.000 -0.4346 0.02916 0.01943 -0.1193 0.7473 0.1278
-9.750 -0.4174 0.02849 0.01873 -0.1187 0.7408 0.1325
-9.500 -0.3979 0.02784 0.01796 -0.1184 0.7353 0.1377
-9.250 -0.3793 0.02722 0.01734 -0.1179 0.7307 0.1427
-9.000 -0.3643 0.02667 0.01674 -0.1166 0.7256 0.1486
-8.750 -0.3500 0.02612 0.01620 -0.1151 0.7203 0.1541
-8.500 -0.3359 0.02563 0.01567 -0.1135 0.7153 0.1602
-8.250 -0.3193 0.02518 0.01514 -0.1121 0.7111 0.1670
-8.000 -0.3073 0.02475 0.01474 -0.1100 0.7068 0.1733
-7.750 -0.2946 0.02442 0.01437 -0.1078 0.7024 0.1812
-7.500 -0.2842 0.02405 0.01407 -0.1053 0.6982 0.1884
-7.250 -0.2701 0.02376 0.01371 -0.1033 0.6943 0.1978
-7.000 -0.2567 0.02339 0.01338 -0.1012 0.6907 0.2070
-6.750 -0.2421 0.02310 0.01307 -0.0992 0.6871 0.2178
-6.500 -0.2312 0.02280 0.01285 -0.0965 0.6828 0.2291
-6.250 -0.2185 0.02250 0.01261 -0.0942 0.6788 0.2416
-6.000 -0.2044 0.02222 0.01236 -0.0920 0.6753 0.2567
-5.750 -0.1893 0.02192 0.01211 -0.0900 0.6721 0.2742
-5.500 -0.1731 0.02163 0.01186 -0.0882 0.6692 0.2948
-5.250 -0.1607 0.02140 0.01175 -0.0857 0.6655 0.3174
-5.000 -0.1485 0.02121 0.01170 -0.0830 0.6615 0.3432
-4.750 -0.1342 0.02104 0.01167 -0.0807 0.6578 0.3712
-4.500 -0.1175 0.02093 0.01165 -0.0787 0.6546 0.4010
-4.250 -0.0984 0.02085 0.01164 -0.0771 0.6516 0.4295
-4.000 -0.0770 0.02082 0.01162 -0.0758 0.6489 0.4567
-3.750 -0.0594 0.02088 0.01170 -0.0739 0.6455 0.4796
-3.500 -0.0435 0.02098 0.01185 -0.0717 0.6414 0.4999
-3.250 -0.0247 0.02107 0.01198 -0.0699 0.6379 0.5184
-3.000 -0.0038 0.02116 0.01207 -0.0685 0.6346 0.5357
-2.750 0.0193 0.02123 0.01211 -0.0675 0.6317 0.5519
-2.500 0.0443 0.02128 0.01210 -0.0668 0.6291 0.5676
-2.250 0.0646 0.02139 0.01216 -0.0654 0.6260 0.5828
-2.000 0.0811 0.02163 0.01251 -0.0632 0.6219 0.5945
-1.750 0.0995 0.02179 0.01267 -0.0614 0.6181 0.6075
-1.500 0.1210 0.02191 0.01278 -0.0601 0.6147 0.6207
-1.250 0.1458 0.02200 0.01286 -0.0593 0.6117 0.6327
-1.000 0.1709 0.02205 0.01285 -0.0586 0.6093 0.6465
-0.750 0.1948 0.02225 0.01306 -0.0577 0.6065 0.6585
-0.500 0.2051 0.02258 0.01349 -0.0545 0.6018 0.6702
-0.250 0.2224 0.02280 0.01374 -0.0525 0.5977 0.6819
0.000 0.2446 0.02292 0.01386 -0.0514 0.5944 0.6920
0.250 0.2699 0.02299 0.01390 -0.0507 0.5916 0.7020
0.500 0.2977 0.02300 0.01386 -0.0506 0.5893 0.7114
0.750 0.3139 0.02328 0.01418 -0.0485 0.5855 0.7199
1.000 0.3203 0.02363 0.01460 -0.0450 0.5804 0.7300
1.250 0.3397 0.02384 0.01485 -0.0434 0.5765 0.7380
1.500 0.3623 0.02389 0.01486 -0.0424 0.5735 0.7485
1.750 0.3919 0.02389 0.01484 -0.0425 0.5710 0.7563
2.000 0.4233 0.02385 0.01474 -0.0429 0.5689 0.7660
2.250 0.4096 0.02464 0.01572 -0.0361 0.5620 0.7761
2.500 0.4226 0.02491 0.01602 -0.0336 0.5577 0.7868
2.750 0.4472 0.02495 0.01606 -0.0330 0.5546 0.7963
3.000 0.4776 0.02489 0.01596 -0.0332 0.5522 0.8064
3.250 0.5123 0.02479 0.01581 -0.0342 0.5502 0.8159
3.500 0.4744 0.02603 0.01726 -0.0239 0.5415 0.8319
3.750 0.4936 0.02620 0.01748 -0.0224 0.5376 0.8425
4.000 0.5229 0.02611 0.01737 -0.0225 0.5349 0.8542
4.250 0.5619 0.02593 0.01715 -0.0241 0.5328 0.8647
4.500 0.5173 0.02760 0.01902 -0.0135 0.5236 0.8867
4.750 0.5425 0.02785 0.01931 -0.0135 0.5195 0.9005
5.000 0.5845 0.02765 0.01910 -0.0159 0.5170 0.9120
5.250 0.6313 0.02734 0.01876 -0.0189 0.5150 0.9233
5.750 0.6693 0.02967 0.02131 -0.0204 0.5012 0.9550
6.000 0.7237 0.02928 0.02092 -0.0247 0.4989 0.9630
6.250 0.7804 0.02877 0.02037 -0.0293 0.4970 0.9699
6.750 0.7579 0.03200 0.02368 -0.0225 0.4816 1.0000
7.000 0.7908 0.03140 0.02302 -0.0226 0.4797 1.0000
7.250 0.8309 0.03064 0.02220 -0.0236 0.4781 1.0000
7.500 0.7555 0.03562 0.02724 -0.0149 0.4629 1.0000
7.750 0.7914 0.03480 0.02639 -0.0150 0.4615 1.0000
8.250 0.7185 0.04386 0.03551 -0.0085 0.4337 1.0000
8.500 0.7422 0.04379 0.03544 -0.0079 0.4305 1.0000
8.750 0.7721 0.04322 0.03485 -0.0076 0.4286 1.0000
9.000 0.8055 0.04238 0.03400 -0.0075 0.4272 1.0000
9.250 0.8426 0.04128 0.03288 -0.0075 0.4260 1.0000
9.750 0.8386 0.04562 0.03726 -0.0050 0.4098 1.0000
10.750 0.8419 0.05418 0.04595 -0.0016 0.3783 1.0000
11.000 0.8748 0.05320 0.04497 -0.0013 0.3765 1.0000
11.250 0.9124 0.05179 0.04355 -0.0011 0.3751 1.0000
11.750 0.9113 0.05654 0.04838 0.0002 0.3592 1.0000
12.000 0.9441 0.05556 0.04741 0.0005 0.3569 1.0000
12.500 0.9481 0.05994 0.05188 0.0014 0.3419 1.0000
13.000 0.9475 0.06509 0.05713 0.0021 0.3264 1.0000
13.250 0.9863 0.06329 0.05532 0.0024 0.3246 1.0000
13.750 0.9851 0.06863 0.06076 0.0028 0.3091 1.0000
14.000 1.0257 0.06654 0.05866 0.0032 0.3071 1.0000
14.250 0.9837 0.07423 0.06647 0.0028 0.2938 1.0000
14.500 1.0213 0.07238 0.06462 0.0033 0.2915 1.0000
15.000 1.0176 0.07838 0.07074 0.0031 0.2764 1.0000
15.250 1.0585 0.07605 0.06837 0.0037 0.2739 1.0000
15.500 1.0160 0.08432 0.07679 0.0026 0.2614 1.0000
15.750 1.0539 0.08223 0.07468 0.0032 0.2587 1.0000
16.000 1.0153 0.09031 0.08289 0.0018 0.2472 1.0000
16.250 1.0479 0.08884 0.08140 0.0023 0.2439 1.0000
16.500 1.0200 0.09569 0.08836 0.0010 0.2339 1.0000
16.750 1.0428 0.09551 0.08820 0.0012 0.2294 1.0000
17.000 1.0833 0.09286 0.08549 0.0020 0.2263 1.0000
17.250 1.0394 0.10210 0.09490 -0.0002 0.2154 1.0000
17.500 1.0746 0.10008 0.09283 0.0005 0.2118 1.0000
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Polar data table (+)
Polar graphs
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