AH 79-K-135/20 B (ah79k135-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-K-135/20 B (ah79k135-il) Reynolds number: 100,000 Max Cl/Cd: 48.02 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79k135-il-100000.txt Download as CSV file: xf-ah79k135-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3566 0.10409 0.09989 -0.0524 0.9853 0.1012
-9.250 -0.3657 0.10056 0.09641 -0.0568 0.9809 0.1055
-9.000 -0.3997 0.09609 0.09201 -0.0675 0.9753 0.1071
-8.750 -0.3631 0.09210 0.08800 -0.0626 0.9750 0.1108
-8.500 -0.3533 0.08893 0.08482 -0.0639 0.9724 0.1152
-8.250 -0.3717 0.08570 0.08164 -0.0664 0.9675 0.1186
-8.000 -0.4055 0.08260 0.07851 -0.0700 0.9618 0.1206
-7.750 -0.4513 0.08156 0.07730 -0.0685 0.9557 0.1217
-7.500 -0.4248 0.07666 0.07257 -0.0674 0.9543 0.1254
-7.250 -0.4213 0.07419 0.07009 -0.0663 0.9510 0.1296
-7.000 -0.4628 0.07264 0.06809 -0.0665 0.9461 0.1372
-6.750 -0.4382 0.06828 0.06399 -0.0654 0.9444 0.1407
-6.500 -0.4447 0.06660 0.06228 -0.0618 0.9409 0.1441
-6.250 -0.4610 0.06436 0.05982 -0.0596 0.9370 0.1537
-6.000 -0.4462 0.06166 0.05713 -0.0587 0.9343 0.1601
-5.750 -0.4368 0.05879 0.05413 -0.0588 0.9317 0.1726
-5.500 -0.4350 0.04624 0.03954 -0.0552 0.9291 0.0637
-5.250 -0.4277 0.04341 0.03651 -0.0526 0.9261 0.0610
-5.000 -0.4133 0.04077 0.03343 -0.0508 0.9233 0.0587
-4.750 -0.3909 0.03846 0.03064 -0.0501 0.9203 0.0587
-4.500 -0.3596 0.03615 0.02781 -0.0506 0.9174 0.0581
-4.250 -0.3339 0.03436 0.02561 -0.0500 0.9145 0.0582
-4.000 -0.3181 0.03321 0.02422 -0.0478 0.9110 0.0591
-3.750 -0.2934 0.03210 0.02290 -0.0471 0.9073 0.0615
-3.500 -0.2614 0.03088 0.02151 -0.0476 0.9038 0.0671
-3.250 -0.2280 0.02979 0.02053 -0.0488 0.9004 0.0837
-3.000 -0.2209 0.02915 0.02001 -0.0455 0.8959 0.1014
-2.750 -0.2023 0.02816 0.01936 -0.0442 0.8917 0.1589
-2.500 -0.1896 0.02557 0.01907 -0.0421 0.8881 0.5300
-2.250 -0.1954 0.02622 0.02073 -0.0316 0.8839 0.8471
-2.000 0.1408 0.02827 0.02148 -0.0816 0.8873 0.9857
-1.750 0.2602 0.02735 0.02018 -0.0998 0.8869 1.0000
-1.500 0.2238 0.02836 0.02121 -0.0898 0.8772 1.0000
-1.250 0.2614 0.02841 0.02110 -0.0925 0.8729 1.0000
-1.000 0.2376 0.02926 0.02193 -0.0847 0.8638 1.0000
-0.750 0.2703 0.02945 0.02199 -0.0864 0.8586 1.0000
-0.500 0.2556 0.03019 0.02271 -0.0801 0.8496 1.0000
-0.250 0.2882 0.03043 0.02284 -0.0816 0.8439 1.0000
0.000 0.2764 0.03115 0.02353 -0.0757 0.8342 1.0000
0.250 0.3171 0.03136 0.02363 -0.0784 0.8289 1.0000
0.500 0.3032 0.03207 0.02431 -0.0720 0.8182 1.0000
0.750 0.3135 0.03260 0.02479 -0.0696 0.8099 1.0000
1.000 0.3399 0.03294 0.02507 -0.0698 0.8029 1.0000
1.250 0.3311 0.03355 0.02565 -0.0642 0.7921 1.0000
1.500 0.3794 0.03378 0.02583 -0.0677 0.7876 1.0000
1.750 0.3664 0.03433 0.02635 -0.0614 0.7762 1.0000
2.000 0.3565 0.03486 0.02686 -0.0557 0.7650 1.0000
2.250 0.4049 0.03502 0.02700 -0.0590 0.7608 1.0000
2.500 0.3896 0.03551 0.02747 -0.0524 0.7488 1.0000
2.750 0.3884 0.03597 0.02789 -0.0482 0.7383 1.0000
3.000 0.4274 0.03608 0.02800 -0.0498 0.7333 1.0000
3.250 0.4237 0.03657 0.02846 -0.0453 0.7219 1.0000
3.500 0.4694 0.03654 0.02847 -0.0477 0.7182 1.0000
3.750 0.4677 0.03709 0.02900 -0.0437 0.7063 1.0000
4.000 0.4788 0.03759 0.02950 -0.0416 0.6962 1.0000
4.250 0.5177 0.03745 0.02940 -0.0429 0.6912 1.0000
4.500 0.5267 0.03804 0.03000 -0.0407 0.6802 1.0000
4.750 0.5712 0.03762 0.02968 -0.0424 0.6765 1.0000
5.000 0.5805 0.03818 0.03026 -0.0403 0.6648 1.0000
5.250 0.6283 0.03742 0.02960 -0.0421 0.6616 1.0000
5.500 0.6390 0.03792 0.03014 -0.0402 0.6498 1.0000
5.750 0.6532 0.03838 0.03069 -0.0386 0.6386 1.0000
6.000 0.6995 0.03733 0.02977 -0.0400 0.6350 1.0000
6.250 0.7131 0.03779 0.03030 -0.0383 0.6232 1.0000
6.500 0.7634 0.03625 0.02896 -0.0398 0.6205 1.0000
7.000 0.7995 0.03644 0.02936 -0.0369 0.5977 1.0000
7.250 0.8506 0.03422 0.02739 -0.0378 0.5941 1.0000
7.500 0.9113 0.03109 0.02453 -0.0392 0.5926 1.0000
7.750 0.9433 0.02964 0.02328 -0.0381 0.5811 1.0000
8.000 1.0033 0.02651 0.02043 -0.0396 0.5704 1.0000
8.250 1.0564 0.02327 0.01729 -0.0398 0.5419 1.0000
8.500 1.0714 0.02231 0.01622 -0.0361 0.5000 1.0000
8.750 1.0767 0.02247 0.01620 -0.0321 0.4591 1.0000
9.000 1.0766 0.02327 0.01691 -0.0283 0.4217 1.0000
9.250 1.0743 0.02441 0.01785 -0.0247 0.3767 1.0000
9.500 1.0662 0.02607 0.01921 -0.0209 0.3201 1.0000
9.750 1.0489 0.02852 0.02111 -0.0166 0.2440 1.0000
10.000 1.0255 0.03182 0.02365 -0.0125 0.1497 1.0000
10.250 1.0048 0.03544 0.02652 -0.0089 0.0840 1.0000
10.500 0.9977 0.03817 0.02905 -0.0065 0.0673 1.0000
10.750 0.9956 0.04057 0.03147 -0.0045 0.0594 1.0000
11.000 0.9927 0.04307 0.03394 -0.0026 0.0549 1.0000
11.250 0.9986 0.04496 0.03592 -0.0010 0.0519 1.0000
11.500 1.0101 0.04655 0.03759 0.0004 0.0492 1.0000
11.750 1.0293 0.04788 0.03891 0.0016 0.0466 1.0000
12.000 1.0894 0.04914 0.03997 0.0015 0.0431 1.0000
12.250 1.1101 0.05092 0.04202 0.0022 0.0419 1.0000
12.500 1.1314 0.05311 0.04449 0.0029 0.0405 1.0000
12.750 1.1517 0.05586 0.04755 0.0035 0.0400 1.0000
13.000 1.1639 0.05909 0.05115 0.0045 0.0401 1.0000
13.250 1.1674 0.06256 0.05495 0.0056 0.0403 1.0000
13.500 1.1651 0.06627 0.05898 0.0069 0.0407 1.0000
13.750 1.1577 0.07021 0.06322 0.0080 0.0410 1.0000
14.000 1.1476 0.07439 0.06768 0.0088 0.0414 1.0000
14.250 1.1359 0.07886 0.07240 0.0093 0.0419 1.0000
14.500 1.1220 0.08375 0.07752 0.0094 0.0423 1.0000
14.750 1.1111 0.08931 0.08326 0.0091 0.0429 1.0000
15.000 1.1034 0.09387 0.08804 0.0087 0.0436 1.0000
15.250 1.0805 0.09808 0.09250 0.0077 0.0442 1.0000
15.500 1.0498 0.10403 0.09872 0.0052 0.0448 1.0000
15.750 1.0105 0.11233 0.10729 0.0005 0.0453 1.0000
16.000 0.9611 0.12447 0.11969 -0.0076 0.0462 1.0000
16.250 0.8903 0.14686 0.14218 -0.0227 0.0491 1.0000
16.500 0.8746 0.15805 0.15333 -0.0284 0.0522 1.0000
16.750 0.8821 0.16123 0.15651 -0.0288 0.0538 1.0000
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