AH 79-K-132/20 (ah79k132-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-132/20 (ah79k132-il) Reynolds number: 100,000 Max Cl/Cd: 45.22 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k132-il-100000-n5.txt Download as CSV file: xf-ah79k132-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-132/20
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.1673 0.12673 0.12155 -0.0669 0.8636 0.0464
-12.750 -0.1640 0.12399 0.11880 -0.0687 0.8627 0.0500
-12.250 -0.2414 0.12483 0.11928 -0.0708 0.8707 0.0444
-12.000 -0.2329 0.12163 0.11605 -0.0724 0.8690 0.0469
-11.750 -0.2269 0.11813 0.11256 -0.0745 0.8672 0.0482
-11.500 -0.2251 0.11295 0.10736 -0.0774 0.8657 0.0382
-11.000 -0.2305 0.10140 0.09590 -0.0850 0.8627 0.0299
-10.750 -0.2242 0.09769 0.09216 -0.0864 0.8614 0.0294
-10.500 -0.2202 0.09367 0.08814 -0.0885 0.8600 0.0292
-10.250 -0.2174 0.08962 0.08411 -0.0907 0.8586 0.0289
-10.000 -0.2165 0.08556 0.08009 -0.0929 0.8568 0.0287
-9.750 -0.2178 0.08118 0.07576 -0.0954 0.8547 0.0286
-9.500 -0.2203 0.07671 0.07133 -0.0982 0.8526 0.0284
-9.250 -0.2260 0.07168 0.06636 -0.1018 0.8505 0.0281
-9.000 -0.2371 0.06632 0.06100 -0.1058 0.8482 0.0279
-8.750 -0.2509 0.06202 0.05669 -0.1070 0.8456 0.0277
-8.500 -0.2655 0.05864 0.05325 -0.1062 0.8429 0.0274
-8.250 -0.2768 0.05481 0.04928 -0.1053 0.8403 0.0274
-8.000 -0.2847 0.05103 0.04530 -0.1040 0.8376 0.0275
-7.750 -0.2901 0.04722 0.04117 -0.1022 0.8348 0.0282
-7.500 -0.2920 0.04349 0.03701 -0.1000 0.8325 0.0290
-7.250 -0.2895 0.04017 0.03307 -0.0976 0.8303 0.0301
-7.000 -0.2823 0.03745 0.03005 -0.0959 0.8277 0.0308
-6.750 -0.2699 0.03539 0.02772 -0.0944 0.8250 0.0316
-6.500 -0.2543 0.03366 0.02569 -0.0931 0.8226 0.0326
-6.250 -0.2365 0.03201 0.02372 -0.0919 0.8204 0.0340
-6.000 -0.2165 0.03039 0.02174 -0.0908 0.8183 0.0359
-5.750 -0.1953 0.02915 0.02013 -0.0898 0.8161 0.0395
-5.500 -0.1752 0.02796 0.01873 -0.0888 0.8132 0.0427
-5.250 -0.1536 0.02712 0.01781 -0.0880 0.8104 0.0458
-5.000 -0.1300 0.02621 0.01665 -0.0872 0.8080 0.0505
-4.750 -0.1064 0.02557 0.01592 -0.0867 0.8058 0.0568
-4.500 -0.0830 0.02518 0.01537 -0.0860 0.8034 0.0647
-4.250 -0.0641 0.02475 0.01498 -0.0849 0.7997 0.0724
-4.000 -0.0420 0.02433 0.01443 -0.0840 0.7966 0.0795
-3.750 -0.0197 0.02389 0.01402 -0.0833 0.7939 0.0885
-3.500 0.0041 0.02348 0.01353 -0.0825 0.7918 0.0972
-3.250 0.0204 0.02334 0.01339 -0.0809 0.7872 0.1055
-3.000 0.0406 0.02311 0.01317 -0.0798 0.7834 0.1172
-2.750 0.0636 0.02286 0.01295 -0.0790 0.7807 0.1380
-2.500 0.0875 0.02249 0.01271 -0.0784 0.7785 0.1738
-2.250 0.0996 0.02224 0.01284 -0.0763 0.7728 0.2514
-2.000 0.1048 0.02085 0.01299 -0.0723 0.7688 0.5927
-1.750 0.1299 0.02124 0.01392 -0.0688 0.7666 0.8118
-1.500 0.1410 0.02170 0.01427 -0.0651 0.7626 0.8607
-1.250 0.1547 0.02216 0.01464 -0.0619 0.7571 0.8907
-1.000 0.1865 0.02243 0.01476 -0.0618 0.7543 0.9170
-0.750 0.3410 0.02254 0.01453 -0.0849 0.7566 0.9659
-0.500 0.3707 0.02252 0.01440 -0.0856 0.7534 0.9716
-0.250 0.4072 0.02241 0.01416 -0.0875 0.7512 0.9747
0.000 0.4325 0.02267 0.01439 -0.0882 0.7447 0.9802
0.250 0.4619 0.02268 0.01432 -0.0890 0.7408 0.9844
0.500 0.4963 0.02256 0.01412 -0.0905 0.7382 0.9873
0.750 0.5221 0.02281 0.01437 -0.0912 0.7318 0.9921
1.000 0.5522 0.02283 0.01435 -0.0922 0.7275 0.9959
1.250 0.5850 0.02269 0.01417 -0.0934 0.7247 0.9991
1.500 0.5963 0.02309 0.01460 -0.0912 0.7172 1.0000
1.750 0.6142 0.02310 0.01460 -0.0895 0.7126 1.0000
2.000 0.6373 0.02294 0.01441 -0.0885 0.7098 1.0000
2.250 0.6389 0.02349 0.01501 -0.0847 0.7003 1.0000
2.500 0.6613 0.02331 0.01481 -0.0836 0.6970 1.0000
2.750 0.6624 0.02382 0.01538 -0.0795 0.6877 1.0000
3.000 0.6842 0.02361 0.01518 -0.0782 0.6841 1.0000
3.250 0.6844 0.02408 0.01568 -0.0739 0.6748 1.0000
3.500 0.7056 0.02384 0.01546 -0.0725 0.6709 1.0000
4.000 0.7250 0.02402 0.01572 -0.0664 0.6575 1.0000
4.500 0.7449 0.02410 0.01587 -0.0602 0.6438 1.0000
5.000 0.7719 0.02408 0.01593 -0.0553 0.6300 1.0000
5.250 0.7785 0.02440 0.01628 -0.0521 0.6204 1.0000
5.500 0.8076 0.02391 0.01589 -0.0518 0.6161 1.0000
5.750 0.8180 0.02421 0.01624 -0.0492 0.6062 1.0000
6.000 0.8504 0.02362 0.01573 -0.0493 0.6017 1.0000
6.250 0.8631 0.02393 0.01611 -0.0472 0.5912 1.0000
6.500 0.9003 0.02315 0.01546 -0.0478 0.5865 1.0000
6.750 0.9136 0.02350 0.01589 -0.0458 0.5751 1.0000
7.000 0.9335 0.02360 0.01608 -0.0446 0.5645 1.0000
7.250 0.9621 0.02325 0.01583 -0.0443 0.5549 1.0000
7.500 0.9933 0.02282 0.01549 -0.0442 0.5442 1.0000
7.750 1.0159 0.02279 0.01557 -0.0432 0.5298 1.0000
8.000 1.0311 0.02310 0.01595 -0.0415 0.5118 1.0000
8.250 1.0500 0.02322 0.01608 -0.0400 0.4906 1.0000
8.500 1.0645 0.02362 0.01649 -0.0383 0.4673 1.0000
8.750 1.0801 0.02403 0.01688 -0.0366 0.4439 1.0000
9.000 1.0918 0.02476 0.01765 -0.0349 0.4226 1.0000
9.250 1.1046 0.02545 0.01835 -0.0332 0.4007 1.0000
9.500 1.1131 0.02638 0.01932 -0.0312 0.3756 1.0000
9.750 1.1148 0.02768 0.02049 -0.0286 0.3397 1.0000
10.000 1.1116 0.02935 0.02190 -0.0258 0.2957 1.0000
10.250 1.1049 0.03137 0.02360 -0.0230 0.2486 1.0000
10.500 1.0957 0.03378 0.02562 -0.0204 0.1961 1.0000
10.750 1.0885 0.03624 0.02775 -0.0181 0.1485 1.0000
11.000 1.0818 0.03885 0.03003 -0.0161 0.1022 1.0000
11.250 1.0749 0.04162 0.03248 -0.0143 0.0642 1.0000
11.500 1.0700 0.04435 0.03505 -0.0127 0.0478 1.0000
11.750 1.0664 0.04710 0.03779 -0.0113 0.0375 1.0000
12.000 1.0664 0.04962 0.04042 -0.0102 0.0294 1.0000
12.250 1.0669 0.05219 0.04306 -0.0094 0.0251 1.0000
12.500 1.0683 0.05477 0.04577 -0.0087 0.0229 1.0000
12.750 1.0678 0.05761 0.04872 -0.0082 0.0209 1.0000
13.000 1.0631 0.06103 0.05220 -0.0078 0.0194 1.0000
13.250 1.0639 0.06391 0.05531 -0.0074 0.0187 1.0000
13.500 1.0650 0.06679 0.05836 -0.0071 0.0180 1.0000
13.750 1.0675 0.06956 0.06127 -0.0069 0.0173 1.0000
14.000 1.0706 0.07230 0.06415 -0.0067 0.0165 1.0000
14.250 1.0743 0.07503 0.06700 -0.0066 0.0157 1.0000
14.500 1.0767 0.07798 0.07005 -0.0068 0.0147 1.0000
14.750 1.0786 0.08103 0.07318 -0.0071 0.0140 1.0000
15.000 1.0815 0.08396 0.07620 -0.0069 0.0133 1.0000
15.250 1.0852 0.08701 0.07945 -0.0072 0.0128 1.0000
15.500 1.0888 0.09018 0.08282 -0.0074 0.0125 1.0000
15.750 1.0910 0.09355 0.08640 -0.0079 0.0124 1.0000
16.000 1.0900 0.09758 0.09067 -0.0087 0.0121 1.0000
16.250 1.0874 0.10188 0.09519 -0.0099 0.0121 1.0000
16.500 1.0821 0.10673 0.10028 -0.0115 0.0120 1.0000
16.750 1.0736 0.11228 0.10607 -0.0137 0.0119 1.0000
17.000 1.0643 0.11808 0.11210 -0.0164 0.0119 1.0000
17.250 1.0533 0.12440 0.11863 -0.0195 0.0119 1.0000
17.500 1.0405 0.13137 0.12582 -0.0234 0.0119 1.0000
17.750 1.0262 0.13903 0.13368 -0.0278 0.0120 1.0000
18.000 1.0114 0.14717 0.14200 -0.0328 0.0121 1.0000
18.250 0.9954 0.15614 0.15112 -0.0384 0.0122 1.0000
18.500 0.9784 0.16610 0.16122 -0.0446 0.0124 1.0000
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