AH 79-K-135/20 B (ah79k135-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AH 79-K-135/20 B (ah79k135-il) Reynolds number: 50,000 Max Cl/Cd: 24.26 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k135-il-50000-n5.txt Download as CSV file: xf-ah79k135-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3433 0.12607 0.11966 -0.0475 1.0000 0.1027
-10.750 -0.3714 0.11571 0.10943 -0.0513 1.0000 0.0521
-10.500 -0.3663 0.11208 0.10582 -0.0521 0.9898 0.0513
-10.250 -0.3609 0.10782 0.10157 -0.0546 0.9827 0.0505
-10.000 -0.3549 0.10360 0.09735 -0.0575 0.9766 0.0491
-9.750 -0.3513 0.09884 0.09260 -0.0611 0.9712 0.0479
-9.500 -0.3501 0.09373 0.08751 -0.0652 0.9657 0.0466
-9.250 -0.3506 0.08760 0.08138 -0.0711 0.9609 0.0451
-8.750 -0.3951 0.07384 0.06728 -0.0838 0.9463 0.0413
-8.500 -0.4001 0.07058 0.06392 -0.0837 0.9406 0.0411
-8.250 -0.4039 0.06713 0.06032 -0.0838 0.9355 0.0408
-8.000 -0.4031 0.06354 0.05653 -0.0842 0.9316 0.0406
-7.750 -0.4089 0.06086 0.05364 -0.0823 0.9263 0.0404
-7.500 -0.4104 0.05789 0.05041 -0.0807 0.9215 0.0403
-7.250 -0.4053 0.05465 0.04681 -0.0800 0.9177 0.0402
-7.000 -0.4023 0.05189 0.04369 -0.0780 0.9136 0.0402
-6.750 -0.4003 0.04957 0.04102 -0.0753 0.9089 0.0403
-6.500 -0.3893 0.04689 0.03789 -0.0739 0.9051 0.0405
-6.250 -0.3719 0.04413 0.03458 -0.0731 0.9022 0.0410
-6.000 -0.3599 0.04205 0.03218 -0.0712 0.8985 0.0421
-5.750 -0.3479 0.04063 0.03062 -0.0694 0.8943 0.0441
-5.500 -0.3273 0.03912 0.02881 -0.0687 0.8909 0.0474
-5.250 -0.2998 0.03729 0.02652 -0.0687 0.8884 0.0508
-5.000 -0.2672 0.03543 0.02436 -0.0693 0.8863 0.0541
-4.750 -0.2553 0.03472 0.02360 -0.0669 0.8817 0.0593
-4.500 -0.2318 0.03370 0.02239 -0.0659 0.8782 0.0672
-4.250 -0.2042 0.03265 0.02123 -0.0659 0.8752 0.0814
-4.000 -0.1756 0.03164 0.02020 -0.0662 0.8725 0.1081
-3.750 -0.1622 0.03098 0.01971 -0.0643 0.8682 0.1400
-3.500 -0.1494 0.03017 0.01915 -0.0621 0.8634 0.1843
-3.250 -0.1360 0.02878 0.01858 -0.0604 0.8595 0.3119
-3.000 -0.1146 0.02783 0.01945 -0.0564 0.8574 0.6826
-2.750 -0.0974 0.02884 0.02039 -0.0520 0.8529 0.8135
-2.500 -0.0664 0.02987 0.02111 -0.0504 0.8492 0.8846
-2.250 0.1270 0.03013 0.02030 -0.0785 0.8571 0.9578
-2.000 0.1862 0.02996 0.01977 -0.0854 0.8545 0.9747
-1.750 0.2322 0.02988 0.01944 -0.0902 0.8504 0.9876
-1.500 0.2793 0.02976 0.01908 -0.0951 0.8469 0.9982
-1.250 0.3077 0.02986 0.01902 -0.0961 0.8429 1.0000
-1.000 0.3082 0.03044 0.01952 -0.0923 0.8353 1.0000
-0.750 0.3261 0.03073 0.01969 -0.0913 0.8299 1.0000
-0.500 0.3311 0.03126 0.02014 -0.0881 0.8227 1.0000
-0.250 0.3462 0.03162 0.02042 -0.0865 0.8167 1.0000
0.000 0.3503 0.03218 0.02092 -0.0832 0.8091 1.0000
0.250 0.3666 0.03255 0.02121 -0.0817 0.8031 1.0000
0.500 0.3652 0.03318 0.02180 -0.0774 0.7944 1.0000
0.750 0.3865 0.03348 0.02203 -0.0767 0.7891 1.0000
1.000 0.3792 0.03415 0.02268 -0.0714 0.7792 1.0000
1.250 0.4056 0.03439 0.02286 -0.0714 0.7747 1.0000
1.500 0.3946 0.03506 0.02350 -0.0656 0.7639 1.0000
2.000 0.4110 0.03587 0.02425 -0.0598 0.7486 1.0000
2.250 0.4046 0.03638 0.02474 -0.0546 0.7387 1.0000
2.500 0.4294 0.03662 0.02495 -0.0543 0.7333 1.0000
2.750 0.4218 0.03714 0.02545 -0.0490 0.7226 1.0000
3.000 0.4517 0.03732 0.02562 -0.0494 0.7181 1.0000
3.250 0.4463 0.03789 0.02617 -0.0447 0.7070 1.0000
3.500 0.4563 0.03835 0.02664 -0.0424 0.6984 1.0000
3.750 0.4785 0.03861 0.02692 -0.0417 0.6916 1.0000
4.000 0.4859 0.03919 0.02750 -0.0392 0.6817 1.0000
4.250 0.5160 0.03930 0.02766 -0.0394 0.6765 1.0000
4.500 0.5229 0.03997 0.02834 -0.0371 0.6657 1.0000
5.000 0.5643 0.04063 0.02914 -0.0355 0.6498 1.0000
5.500 0.6094 0.04114 0.02982 -0.0343 0.6341 1.0000
5.750 0.6198 0.04186 0.03065 -0.0326 0.6225 1.0000
6.000 0.6346 0.04247 0.03134 -0.0313 0.6119 1.0000
6.250 0.6675 0.04219 0.03121 -0.0315 0.6061 1.0000
6.500 0.6803 0.04287 0.03200 -0.0300 0.5942 1.0000
6.750 0.6966 0.04341 0.03269 -0.0289 0.5832 1.0000
7.000 0.7312 0.04282 0.03230 -0.0289 0.5773 1.0000
7.250 0.7448 0.04350 0.03311 -0.0276 0.5649 1.0000
7.500 0.7614 0.04398 0.03375 -0.0264 0.5531 1.0000
7.750 0.7964 0.04308 0.03311 -0.0261 0.5470 1.0000
8.000 0.8143 0.04337 0.03359 -0.0248 0.5347 1.0000
8.250 0.8315 0.04372 0.03413 -0.0236 0.5220 1.0000
8.500 0.8517 0.04381 0.03443 -0.0224 0.5094 1.0000
8.750 0.8749 0.04362 0.03450 -0.0212 0.4972 1.0000
9.000 0.9020 0.04304 0.03419 -0.0202 0.4849 1.0000
9.250 0.9273 0.04257 0.03397 -0.0189 0.4707 1.0000
9.500 0.9476 0.04241 0.03405 -0.0174 0.4531 1.0000
9.750 0.9771 0.04106 0.03295 -0.0157 0.4312 1.0000
10.000 0.9913 0.04087 0.03284 -0.0133 0.4008 1.0000
10.250 0.9935 0.04176 0.03371 -0.0107 0.3627 1.0000
10.500 0.9922 0.04288 0.03455 -0.0080 0.3116 1.0000
10.750 0.9850 0.04497 0.03625 -0.0056 0.2551 1.0000
11.000 0.9746 0.04780 0.03864 -0.0037 0.1976 1.0000
11.250 0.9642 0.05107 0.04153 -0.0024 0.1469 1.0000
11.500 0.9541 0.05464 0.04477 -0.0014 0.1086 1.0000
11.750 0.9449 0.05843 0.04831 -0.0007 0.0827 1.0000
12.000 0.9386 0.06211 0.05184 -0.0003 0.0686 1.0000
12.250 0.9350 0.06559 0.05532 0.0000 0.0603 1.0000
12.500 0.9317 0.06911 0.05882 0.0001 0.0550 1.0000
12.750 0.9334 0.07207 0.06190 0.0005 0.0512 1.0000
13.000 0.9367 0.07488 0.06484 0.0009 0.0477 1.0000
13.250 0.9411 0.07756 0.06758 0.0011 0.0451 1.0000
13.500 0.9480 0.07998 0.07007 0.0017 0.0423 1.0000
13.750 0.9578 0.08225 0.07263 0.0022 0.0394 1.0000
14.000 0.9671 0.08462 0.07521 0.0026 0.0373 1.0000
14.250 0.9764 0.08705 0.07781 0.0029 0.0356 1.0000
14.500 0.9881 0.08934 0.08025 0.0034 0.0344 1.0000
15.000 1.0039 0.09559 0.08698 0.0035 0.0330 1.0000
15.250 0.9998 0.10033 0.09203 0.0023 0.0328 1.0000
15.500 0.9922 0.10563 0.09762 0.0004 0.0326 1.0000
15.750 0.9817 0.11152 0.10378 -0.0021 0.0326 1.0000
16.000 0.9693 0.11797 0.11045 -0.0052 0.0326 1.0000
16.250 0.9553 0.12501 0.11769 -0.0090 0.0327 1.0000
16.500 0.9415 0.13245 0.12531 -0.0132 0.0329 1.0000
16.750 0.9270 0.14051 0.13351 -0.0179 0.0330 1.0000
17.000 0.9143 0.14872 0.14182 -0.0228 0.0333 1.0000
17.250 0.8904 0.16158 0.15480 -0.0307 0.0341 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 79-K-135/20 B (ah79k135-il)