AH 79-K-135/20 B (ah79k135-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-135/20 B (ah79k135-il) Reynolds number: 100,000 Max Cl/Cd: 46.32 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k135-il-100000-n5.txt Download as CSV file: xf-ah79k135-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-135/20 B
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2917 0.11370 0.10829 -0.0693 0.8834 0.0309
-11.500 -0.2825 0.11026 0.10484 -0.0703 0.8813 0.0297
-11.250 -0.2772 0.10628 0.10086 -0.0723 0.8793 0.0284
-10.750 -0.2870 0.09286 0.08749 -0.0809 0.8755 0.0242
-10.500 -0.2829 0.08900 0.08364 -0.0830 0.8738 0.0239
-10.250 -0.2818 0.08443 0.07907 -0.0858 0.8719 0.0237
-10.000 -0.2807 0.08024 0.07491 -0.0884 0.8697 0.0233
-9.750 -0.2850 0.07468 0.06939 -0.0924 0.8672 0.0230
-9.500 -0.2947 0.06813 0.06284 -0.0978 0.8644 0.0226
-9.250 -0.3087 0.06287 0.05752 -0.1009 0.8617 0.0223
-9.000 -0.3242 0.05868 0.05322 -0.1017 0.8590 0.0220
-8.750 -0.3406 0.05538 0.04977 -0.1003 0.8563 0.0218
-8.500 -0.3522 0.05201 0.04624 -0.0986 0.8533 0.0215
-8.250 -0.3593 0.04864 0.04259 -0.0967 0.8505 0.0213
-8.000 -0.3619 0.04537 0.03901 -0.0948 0.8480 0.0210
-7.750 -0.3603 0.04227 0.03552 -0.0927 0.8455 0.0210
-7.500 -0.3548 0.03934 0.03217 -0.0906 0.8431 0.0210
-7.250 -0.3453 0.03674 0.02914 -0.0887 0.8409 0.0210
-7.000 -0.3330 0.03445 0.02645 -0.0869 0.8386 0.0213
-6.750 -0.3171 0.03261 0.02425 -0.0855 0.8361 0.0223
-6.500 -0.2984 0.03089 0.02212 -0.0842 0.8336 0.0233
-6.250 -0.2776 0.02930 0.02019 -0.0832 0.8313 0.0247
-6.000 -0.2558 0.02808 0.01882 -0.0826 0.8293 0.0258
-5.750 -0.2325 0.02694 0.01752 -0.0819 0.8275 0.0270
-5.500 -0.2116 0.02596 0.01642 -0.0809 0.8246 0.0284
-5.250 -0.1906 0.02505 0.01539 -0.0798 0.8218 0.0304
-5.000 -0.1704 0.02424 0.01450 -0.0786 0.8191 0.0328
-4.750 -0.1490 0.02371 0.01389 -0.0777 0.8167 0.0387
-4.500 -0.1283 0.02304 0.01319 -0.0766 0.8145 0.0472
-4.250 -0.1105 0.02253 0.01269 -0.0751 0.8112 0.0640
-4.000 -0.0922 0.02205 0.01234 -0.0738 0.8077 0.0907
-3.750 -0.0727 0.02152 0.01207 -0.0727 0.8048 0.1384
-3.500 -0.0529 0.02087 0.01175 -0.0716 0.8023 0.2159
-3.250 -0.0397 0.02014 0.01165 -0.0696 0.7987 0.3597
-3.000 -0.0298 0.01949 0.01177 -0.0665 0.7945 0.5351
-2.750 -0.0079 0.01950 0.01235 -0.0638 0.7917 0.6981
-2.500 0.0179 0.01995 0.01280 -0.0619 0.7894 0.7761
-2.250 0.0356 0.02051 0.01328 -0.0591 0.7857 0.8205
-2.000 0.0521 0.02110 0.01379 -0.0562 0.7810 0.8536
-1.750 0.0782 0.02154 0.01409 -0.0548 0.7779 0.8793
-1.500 0.1163 0.02187 0.01424 -0.0558 0.7758 0.9007
-1.250 0.1572 0.02208 0.01428 -0.0578 0.7737 0.9160
-1.000 0.1909 0.02231 0.01442 -0.0595 0.7685 0.9261
-0.750 0.2234 0.02239 0.01437 -0.0606 0.7649 0.9348
-0.500 0.2658 0.02236 0.01421 -0.0637 0.7624 0.9398
-0.250 0.2933 0.02240 0.01416 -0.0639 0.7591 0.9471
0.000 0.3262 0.02256 0.01427 -0.0658 0.7533 0.9518
0.250 0.3581 0.02256 0.01420 -0.0670 0.7497 0.9572
0.500 0.3920 0.02248 0.01405 -0.0684 0.7470 0.9616
0.750 0.4218 0.02267 0.01424 -0.0697 0.7408 0.9667
1.000 0.4506 0.02269 0.01423 -0.0704 0.7363 0.9718
1.250 0.4855 0.02255 0.01405 -0.0720 0.7332 0.9751
1.500 0.5135 0.02274 0.01426 -0.0730 0.7267 0.9798
1.750 0.5421 0.02274 0.01427 -0.0736 0.7218 0.9843
2.000 0.5771 0.02254 0.01406 -0.0751 0.7188 0.9871
2.250 0.6031 0.02281 0.01440 -0.0759 0.7111 0.9920
2.500 0.6344 0.02270 0.01432 -0.0768 0.7066 0.9956
2.750 0.6689 0.02241 0.01405 -0.0781 0.7038 0.9986
3.000 0.6775 0.02284 0.01455 -0.0756 0.6940 1.0000
3.250 0.6998 0.02258 0.01434 -0.0744 0.6904 1.0000
3.500 0.7022 0.02300 0.01482 -0.0705 0.6805 1.0000
3.750 0.7245 0.02269 0.01454 -0.0692 0.6767 1.0000
4.000 0.7252 0.02308 0.01499 -0.0650 0.6665 1.0000
4.250 0.7481 0.02267 0.01466 -0.0637 0.6627 1.0000
4.500 0.7467 0.02303 0.01507 -0.0590 0.6521 1.0000
4.750 0.7717 0.02254 0.01464 -0.0579 0.6483 1.0000
5.250 0.7776 0.02286 0.01506 -0.0496 0.6284 1.0000
5.500 0.7990 0.02248 0.01478 -0.0480 0.6217 1.0000
5.750 0.8079 0.02262 0.01498 -0.0450 0.6113 1.0000
6.000 0.8405 0.02198 0.01443 -0.0450 0.6058 1.0000
6.250 0.8511 0.02218 0.01471 -0.0423 0.5941 1.0000
6.500 0.8689 0.02215 0.01478 -0.0405 0.5832 1.0000
6.750 0.8951 0.02185 0.01458 -0.0398 0.5726 1.0000
7.000 0.9241 0.02148 0.01430 -0.0395 0.5609 1.0000
7.250 0.9473 0.02136 0.01427 -0.0384 0.5464 1.0000
7.500 0.9646 0.02144 0.01444 -0.0366 0.5277 1.0000
7.750 0.9864 0.02138 0.01440 -0.0353 0.5063 1.0000
8.000 1.0020 0.02163 0.01465 -0.0333 0.4822 1.0000
8.250 1.0137 0.02199 0.01490 -0.0308 0.4474 1.0000
8.500 1.0192 0.02277 0.01550 -0.0279 0.4072 1.0000
8.750 1.0177 0.02401 0.01643 -0.0246 0.3536 1.0000
9.000 1.0132 0.02563 0.01765 -0.0214 0.2957 1.0000
9.250 1.0085 0.02745 0.01909 -0.0185 0.2409 1.0000
9.500 1.0072 0.02925 0.02061 -0.0160 0.1926 1.0000
9.750 1.0035 0.03134 0.02233 -0.0137 0.1386 1.0000
10.000 0.9995 0.03361 0.02421 -0.0114 0.0841 1.0000
10.250 0.9954 0.03601 0.02626 -0.0093 0.0501 1.0000
10.500 0.9976 0.03800 0.02823 -0.0076 0.0380 1.0000
10.750 1.0005 0.03998 0.03024 -0.0061 0.0315 1.0000
11.000 1.0050 0.04187 0.03225 -0.0049 0.0281 1.0000
11.250 1.0079 0.04391 0.03441 -0.0037 0.0262 1.0000
11.500 1.0105 0.04605 0.03666 -0.0026 0.0251 1.0000
11.750 1.0131 0.04825 0.03902 -0.0016 0.0241 1.0000
12.000 1.0156 0.05051 0.04143 -0.0007 0.0232 1.0000
12.250 1.0183 0.05283 0.04388 0.0000 0.0225 1.0000
12.500 1.0213 0.05520 0.04637 0.0007 0.0218 1.0000
12.750 1.0252 0.05754 0.04882 0.0013 0.0213 1.0000
13.000 1.0300 0.05985 0.05122 0.0018 0.0207 1.0000
13.250 1.0358 0.06211 0.05356 0.0023 0.0202 1.0000
13.500 1.0428 0.06433 0.05581 0.0030 0.0194 1.0000
13.750 1.0516 0.06646 0.05816 0.0034 0.0186 1.0000
14.000 1.0598 0.06874 0.06063 0.0038 0.0179 1.0000
14.250 1.0684 0.07109 0.06316 0.0041 0.0174 1.0000
14.500 1.0758 0.07370 0.06597 0.0044 0.0171 1.0000
14.750 1.0809 0.07663 0.06911 0.0045 0.0169 1.0000
15.000 1.0830 0.07999 0.07270 0.0044 0.0167 1.0000
15.250 1.0819 0.08379 0.07674 0.0040 0.0165 1.0000
15.500 1.0779 0.08804 0.08123 0.0032 0.0164 1.0000
15.750 1.0709 0.09273 0.08617 0.0019 0.0163 1.0000
16.000 1.0613 0.09795 0.09164 0.0002 0.0163 1.0000
16.250 1.0496 0.10367 0.09761 -0.0021 0.0163 1.0000
16.500 1.0352 0.11011 0.10430 -0.0050 0.0164 1.0000
16.750 1.0193 0.11709 0.11150 -0.0086 0.0164 1.0000
17.000 1.0010 0.12500 0.11964 -0.0131 0.0166 1.0000
17.250 0.9807 0.13390 0.12875 -0.0184 0.0167 1.0000
17.500 0.9579 0.14420 0.13923 -0.0249 0.0170 1.0000
17.750 0.9325 0.15632 0.15149 -0.0325 0.0173 1.0000
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Polar data table (+)
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