AH 79-K-135/20 B (ah79k135-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-135/20 B (ah79k135-il) Reynolds number: 500,000 Max Cl/Cd: 95.02 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k135-il-500000-n5.txt Download as CSV file: xf-ah79k135-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3070 0.08775 0.08432 -0.0794 0.7711 0.0071
-11.000 -0.3185 0.08116 0.07777 -0.0824 0.7703 0.0072
-10.750 -0.3285 0.07532 0.07198 -0.0856 0.7694 0.0070
-10.500 -0.3569 0.06464 0.06137 -0.0922 0.7683 0.0070
-10.000 -0.4485 0.04360 0.03996 -0.0998 0.7652 0.0068
-9.750 -0.4798 0.03932 0.03545 -0.0955 0.7637 0.0067
-9.500 -0.5020 0.03558 0.03139 -0.0907 0.7626 0.0067
-9.250 -0.5114 0.03211 0.02755 -0.0871 0.7616 0.0067
-9.000 -0.5084 0.02965 0.02474 -0.0845 0.7607 0.0069
-8.750 -0.5022 0.02726 0.02202 -0.0821 0.7597 0.0069
-8.500 -0.4892 0.02559 0.02006 -0.0804 0.7585 0.0071
-8.250 -0.4737 0.02413 0.01834 -0.0789 0.7572 0.0072
-8.000 -0.4568 0.02265 0.01663 -0.0776 0.7561 0.0072
-7.750 -0.4379 0.02134 0.01510 -0.0765 0.7550 0.0072
-7.500 -0.4176 0.02015 0.01372 -0.0755 0.7538 0.0072
-7.250 -0.3961 0.01914 0.01254 -0.0747 0.7526 0.0073
-7.000 -0.3739 0.01819 0.01144 -0.0739 0.7514 0.0073
-6.750 -0.3511 0.01740 0.01053 -0.0733 0.7504 0.0073
-6.500 -0.3281 0.01666 0.00970 -0.0727 0.7494 0.0074
-6.250 -0.3067 0.01570 0.00864 -0.0718 0.7484 0.0076
-6.000 -0.2840 0.01500 0.00787 -0.0711 0.7474 0.0078
-5.750 -0.2603 0.01448 0.00728 -0.0705 0.7465 0.0081
-5.500 -0.2363 0.01402 0.00679 -0.0700 0.7452 0.0084
-5.250 -0.2119 0.01361 0.00635 -0.0695 0.7436 0.0089
-5.000 -0.1872 0.01324 0.00594 -0.0691 0.7420 0.0093
-4.750 -0.1620 0.01291 0.00556 -0.0688 0.7405 0.0098
-4.500 -0.1366 0.01260 0.00520 -0.0684 0.7390 0.0104
-4.250 -0.1114 0.01225 0.00482 -0.0681 0.7375 0.0117
-4.000 -0.0855 0.01198 0.00451 -0.0678 0.7361 0.0136
-3.750 -0.0600 0.01165 0.00420 -0.0675 0.7348 0.0199
-3.500 -0.0344 0.01134 0.00396 -0.0673 0.7335 0.0410
-3.250 -0.0079 0.01112 0.00375 -0.0672 0.7323 0.0519
-3.000 0.0177 0.01088 0.00361 -0.0670 0.7306 0.0721
-2.750 0.0419 0.01048 0.00345 -0.0666 0.7284 0.1288
-2.500 0.0658 0.01004 0.00330 -0.0662 0.7263 0.2034
-2.250 0.0906 0.00969 0.00315 -0.0659 0.7242 0.2687
-2.000 0.1152 0.00929 0.00299 -0.0656 0.7223 0.3472
-1.750 0.1382 0.00876 0.00281 -0.0650 0.7206 0.4565
-1.500 0.1602 0.00821 0.00266 -0.0642 0.7189 0.5774
-1.250 0.1831 0.00784 0.00261 -0.0633 0.7170 0.6738
-1.000 0.2068 0.00768 0.00270 -0.0623 0.7141 0.7442
-0.750 0.2326 0.00764 0.00277 -0.0618 0.7113 0.7829
-0.500 0.2592 0.00765 0.00282 -0.0614 0.7087 0.8068
-0.250 0.2858 0.00768 0.00285 -0.0610 0.7062 0.8296
0.000 0.3126 0.00773 0.00287 -0.0606 0.7039 0.8456
0.250 0.3390 0.00779 0.00297 -0.0602 0.7005 0.8535
0.500 0.3661 0.00783 0.00299 -0.0601 0.6968 0.8611
0.750 0.3933 0.00783 0.00300 -0.0600 0.6935 0.8654
1.000 0.4210 0.00782 0.00296 -0.0600 0.6905 0.8695
1.250 0.4485 0.00784 0.00297 -0.0600 0.6865 0.8742
1.500 0.4757 0.00784 0.00299 -0.0600 0.6817 0.8775
1.750 0.5032 0.00782 0.00296 -0.0599 0.6775 0.8802
2.000 0.5305 0.00782 0.00297 -0.0599 0.6725 0.8830
2.250 0.5579 0.00782 0.00298 -0.0600 0.6665 0.8859
2.500 0.5855 0.00781 0.00294 -0.0600 0.6609 0.8888
2.750 0.6126 0.00782 0.00297 -0.0600 0.6533 0.8913
3.000 0.6393 0.00781 0.00296 -0.0599 0.6454 0.8934
3.250 0.6655 0.00783 0.00297 -0.0596 0.6348 0.8958
3.500 0.6914 0.00786 0.00298 -0.0593 0.6220 0.8984
3.750 0.7171 0.00793 0.00302 -0.0591 0.6091 0.9010
4.000 0.7427 0.00802 0.00308 -0.0588 0.5963 0.9038
4.250 0.7671 0.00814 0.00317 -0.0582 0.5814 0.9061
4.500 0.7896 0.00831 0.00328 -0.0573 0.5617 0.9085
4.750 0.8111 0.00854 0.00343 -0.0562 0.5369 0.9113
5.000 0.8304 0.00885 0.00364 -0.0548 0.5066 0.9145
5.250 0.8477 0.00926 0.00389 -0.0530 0.4704 0.9181
5.500 0.8615 0.00975 0.00420 -0.0506 0.4292 0.9215
5.750 0.8742 0.01027 0.00455 -0.0481 0.3877 0.9253
6.000 0.8850 0.01086 0.00495 -0.0453 0.3441 0.9296
6.250 0.8955 0.01143 0.00535 -0.0425 0.3051 0.9340
6.500 0.9000 0.01209 0.00582 -0.0387 0.2603 0.9392
6.750 0.9055 0.01265 0.00625 -0.0350 0.2294 0.9454
7.000 0.9122 0.01330 0.00678 -0.0318 0.1983 0.9525
7.250 0.9192 0.01423 0.00752 -0.0292 0.1559 0.9616
7.500 0.9308 0.01578 0.00873 -0.0288 0.0915 0.9725
7.750 0.9431 0.01740 0.01008 -0.0288 0.0417 1.0000
8.000 0.9540 0.01839 0.01098 -0.0273 0.0218 1.0000
8.250 0.9654 0.01935 0.01190 -0.0259 0.0125 1.0000
8.500 0.9800 0.02013 0.01270 -0.0247 0.0107 1.0000
8.750 0.9950 0.02088 0.01349 -0.0237 0.0098 1.0000
9.000 1.0099 0.02165 0.01430 -0.0227 0.0091 1.0000
9.250 1.0238 0.02248 0.01517 -0.0216 0.0086 1.0000
9.500 1.0373 0.02335 0.01609 -0.0204 0.0082 1.0000
9.750 1.0495 0.02432 0.01711 -0.0192 0.0079 1.0000
10.000 1.0602 0.02540 0.01826 -0.0179 0.0076 1.0000
10.250 1.0714 0.02646 0.01938 -0.0167 0.0075 1.0000
10.500 1.0827 0.02753 0.02052 -0.0155 0.0073 1.0000
10.750 1.0930 0.02870 0.02176 -0.0143 0.0072 1.0000
11.000 1.1020 0.02997 0.02310 -0.0131 0.0070 1.0000
11.250 1.1104 0.03131 0.02451 -0.0118 0.0070 1.0000
11.500 1.1187 0.03269 0.02596 -0.0107 0.0068 1.0000
11.750 1.1253 0.03422 0.02758 -0.0095 0.0066 1.0000
12.000 1.1319 0.03580 0.02923 -0.0084 0.0065 1.0000
12.250 1.1376 0.03750 0.03100 -0.0073 0.0065 1.0000
12.500 1.1431 0.03926 0.03286 -0.0063 0.0064 1.0000
12.750 1.1477 0.04119 0.03487 -0.0053 0.0062 1.0000
13.000 1.1519 0.04322 0.03699 -0.0045 0.0062 1.0000
13.250 1.1590 0.04502 0.03885 -0.0040 0.0060 1.0000
13.500 1.1621 0.04727 0.04119 -0.0032 0.0059 1.0000
13.750 1.1656 0.04954 0.04354 -0.0027 0.0058 1.0000
14.000 1.1696 0.05180 0.04586 -0.0023 0.0056 1.0000
14.250 1.1728 0.05420 0.04833 -0.0020 0.0055 1.0000
14.500 1.1731 0.05694 0.05115 -0.0015 0.0053 1.0000
14.750 1.1763 0.05944 0.05377 -0.0013 0.0054 1.0000
15.000 1.1754 0.06241 0.05684 -0.0008 0.0052 1.0000
15.250 1.1772 0.06518 0.05972 -0.0007 0.0052 1.0000
15.500 1.1800 0.06797 0.06264 -0.0010 0.0051 1.0000
15.750 1.1812 0.07099 0.06579 -0.0012 0.0051 1.0000
16.000 1.1821 0.07414 0.06907 -0.0017 0.0050 1.0000
16.250 1.1813 0.07755 0.07260 -0.0022 0.0050 1.0000
16.500 1.1807 0.08110 0.07630 -0.0032 0.0050 1.0000
16.750 1.1779 0.08497 0.08031 -0.0040 0.0050 1.0000
17.000 1.1749 0.08902 0.08450 -0.0053 0.0049 1.0000
17.250 1.1698 0.09350 0.08914 -0.0067 0.0049 1.0000
17.500 1.1644 0.09817 0.09397 -0.0085 0.0048 1.0000
17.750 1.1573 0.10316 0.09911 -0.0105 0.0048 1.0000
18.000 1.1490 0.10858 0.10470 -0.0128 0.0047 1.0000
18.250 1.1398 0.11422 0.11049 -0.0154 0.0048 1.0000
18.500 1.1311 0.12001 0.11642 -0.0183 0.0048 1.0000
18.750 1.1208 0.12624 0.12282 -0.0216 0.0047 1.0000
19.000 1.1098 0.13278 0.12951 -0.0252 0.0047 1.0000
19.250 1.0965 0.14006 0.13696 -0.0293 0.0047 1.0000
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Polar data table (+)
Polar graphs
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