AH 93-K-132/15 (ah93k132-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-K-132/15 (ah93k132-il) Reynolds number: 200,000 Max Cl/Cd: 73.4 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93k132-il-200000.txt Download as CSV file: xf-ah93k132-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-132/15
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2939 0.09518 0.09186 -0.0751 0.8900 0.0441
-9.250 -0.2971 0.08983 0.08651 -0.0831 0.8884 0.0443
-9.000 -0.3037 0.08548 0.08208 -0.0879 0.8869 0.0444
-8.750 -0.3119 0.08209 0.07859 -0.0903 0.8858 0.0445
-8.500 -0.3108 0.07536 0.07195 -0.0916 0.8847 0.0457
-8.250 -0.2997 0.07280 0.06941 -0.0914 0.8831 0.0467
-8.000 -0.2942 0.07012 0.06671 -0.0921 0.8815 0.0478
-7.750 -0.2914 0.06729 0.06381 -0.0929 0.8798 0.0491
-7.500 -0.2905 0.06445 0.06088 -0.0930 0.8774 0.0507
-7.250 -0.2903 0.06164 0.05792 -0.0924 0.8753 0.0528
-7.000 -0.2988 0.06147 0.05710 -0.0891 0.8730 0.0569
-6.750 -0.2698 0.04113 0.03729 -0.0884 0.8651 0.0591
-6.500 -0.2947 0.05332 0.04893 -0.0873 0.8675 0.0595
-6.250 -0.2859 0.05156 0.04715 -0.0856 0.8648 0.0613
-6.000 -0.2761 0.04983 0.04527 -0.0835 0.8620 0.0643
-5.500 -0.2794 0.04666 0.04156 -0.0758 0.8536 0.0732
-5.250 -0.2626 0.04481 0.03966 -0.0745 0.8506 0.0763
-4.750 -0.2493 0.03667 0.02975 -0.0625 0.8411 0.0341
-4.500 -0.2232 0.03408 0.02687 -0.0618 0.8384 0.0327
-4.250 -0.2057 0.03351 0.02599 -0.0596 0.8332 0.0335
-4.000 -0.1908 0.03142 0.02366 -0.0576 0.8285 0.0352
-3.750 -0.1598 0.03006 0.02216 -0.0578 0.8258 0.0364
-3.500 -0.1251 0.02904 0.02103 -0.0584 0.8239 0.0383
-3.250 -0.1200 0.02867 0.02061 -0.0548 0.8158 0.0400
-3.000 -0.0915 0.02834 0.02018 -0.0546 0.8125 0.0446
-2.750 -0.0626 0.02726 0.01915 -0.0544 0.8105 0.0523
-2.500 -0.0552 0.02704 0.01889 -0.0512 0.8028 0.0586
-2.250 -0.0321 0.02644 0.01837 -0.0502 0.7990 0.0845
-2.000 -0.0180 0.02434 0.01794 -0.0480 0.7966 0.4429
-1.750 0.1649 0.02504 0.01997 -0.0750 0.8019 0.9701
-1.500 0.2956 0.02475 0.01938 -0.0948 0.8050 0.9951
-1.250 0.3383 0.02470 0.01921 -0.0986 0.8010 1.0000
-1.000 0.3585 0.02473 0.01915 -0.0972 0.7975 1.0000
-0.750 0.3796 0.02477 0.01910 -0.0956 0.7953 1.0000
-0.500 0.3919 0.02517 0.01946 -0.0945 0.7862 1.0000
-0.250 0.4137 0.02515 0.01937 -0.0932 0.7831 1.0000
0.000 0.4368 0.02509 0.01924 -0.0918 0.7811 1.0000
0.250 0.4470 0.02556 0.01969 -0.0903 0.7716 1.0000
0.500 0.4707 0.02544 0.01952 -0.0892 0.7688 1.0000
0.750 0.4955 0.02530 0.01932 -0.0881 0.7671 1.0000
1.000 0.5047 0.02578 0.01980 -0.0862 0.7572 1.0000
1.250 0.5299 0.02558 0.01956 -0.0853 0.7548 1.0000
1.500 0.5553 0.02537 0.01932 -0.0843 0.7527 1.0000
1.750 0.5650 0.02580 0.01976 -0.0823 0.7430 1.0000
2.000 0.5921 0.02548 0.01942 -0.0816 0.7410 1.0000
2.250 0.6024 0.02588 0.01984 -0.0794 0.7319 1.0000
2.500 0.6291 0.02553 0.01949 -0.0787 0.7291 1.0000
2.750 0.6578 0.02504 0.01899 -0.0781 0.7272 1.0000
3.000 0.6687 0.02539 0.01937 -0.0759 0.7176 1.0000
3.250 0.6974 0.02486 0.01886 -0.0754 0.7152 1.0000
3.500 0.7275 0.02420 0.01822 -0.0749 0.7137 1.0000
3.750 0.7388 0.02457 0.01862 -0.0728 0.7036 1.0000
4.000 0.7687 0.02390 0.01800 -0.0724 0.7016 1.0000
4.250 0.7993 0.02311 0.01727 -0.0719 0.7001 1.0000
4.500 0.8125 0.02337 0.01758 -0.0700 0.6899 1.0000
4.750 0.8439 0.02248 0.01675 -0.0696 0.6879 1.0000
5.000 0.8758 0.02146 0.01579 -0.0692 0.6866 1.0000
5.250 0.8918 0.02151 0.01593 -0.0675 0.6764 1.0000
5.500 0.9249 0.02026 0.01475 -0.0671 0.6745 1.0000
5.750 0.9590 0.01889 0.01346 -0.0667 0.6727 1.0000
6.000 0.9798 0.01856 0.01323 -0.0654 0.6618 1.0000
6.250 1.0072 0.01767 0.01242 -0.0644 0.6521 1.0000
6.500 1.0414 0.01632 0.01111 -0.0639 0.6442 1.0000
6.750 1.0654 0.01589 0.01073 -0.0627 0.6288 1.0000
7.000 1.0873 0.01567 0.01057 -0.0614 0.6091 1.0000
7.250 1.1121 0.01529 0.01014 -0.0601 0.5877 1.0000
7.500 1.1303 0.01540 0.01021 -0.0583 0.5608 1.0000
7.750 1.1458 0.01567 0.01037 -0.0561 0.5303 1.0000
8.000 1.1554 0.01622 0.01080 -0.0532 0.4974 1.0000
8.250 1.1582 0.01701 0.01148 -0.0495 0.4629 1.0000
8.500 1.1518 0.01789 0.01221 -0.0442 0.4314 1.0000
8.750 1.1410 0.01878 0.01294 -0.0382 0.4010 1.0000
9.000 1.1316 0.01983 0.01379 -0.0327 0.3671 1.0000
9.250 1.1239 0.02101 0.01478 -0.0279 0.3299 1.0000
9.500 1.1168 0.02238 0.01593 -0.0235 0.2913 1.0000
9.750 1.1108 0.02392 0.01723 -0.0196 0.2506 1.0000
10.000 1.1057 0.02560 0.01866 -0.0161 0.2083 1.0000
10.250 1.1014 0.02740 0.02020 -0.0130 0.1674 1.0000
10.500 1.0988 0.02923 0.02181 -0.0102 0.1322 1.0000
10.750 1.0973 0.03110 0.02350 -0.0077 0.1049 1.0000
11.000 1.0951 0.03311 0.02538 -0.0053 0.0857 1.0000
11.250 1.0956 0.03504 0.02725 -0.0032 0.0706 1.0000
11.500 1.0955 0.03713 0.02930 -0.0011 0.0596 1.0000
11.750 1.0986 0.03903 0.03121 0.0005 0.0512 1.0000
12.000 1.1015 0.04101 0.03325 0.0022 0.0454 1.0000
12.250 1.1051 0.04297 0.03524 0.0037 0.0411 1.0000
12.500 1.1076 0.04507 0.03736 0.0055 0.0377 1.0000
12.750 1.1158 0.04672 0.03913 0.0066 0.0345 1.0000
13.000 1.1223 0.04854 0.04099 0.0077 0.0318 1.0000
13.250 1.1318 0.05031 0.04272 0.0098 0.0295 1.0000
13.500 1.1427 0.05191 0.04454 0.0109 0.0282 1.0000
13.750 1.1527 0.05365 0.04643 0.0120 0.0265 1.0000
14.000 1.1597 0.05559 0.04849 0.0128 0.0249 1.0000
14.250 1.1665 0.05759 0.05054 0.0136 0.0235 1.0000
14.500 1.1816 0.05994 0.05300 0.0152 0.0222 1.0000
14.750 1.1849 0.06305 0.05638 0.0164 0.0217 1.0000
15.000 1.1833 0.06615 0.05974 0.0173 0.0214 1.0000
15.250 1.1790 0.06968 0.06355 0.0181 0.0212 1.0000
15.500 1.1715 0.07361 0.06775 0.0186 0.0210 1.0000
15.750 1.1611 0.07793 0.07233 0.0187 0.0208 1.0000
16.000 1.1483 0.08267 0.07733 0.0184 0.0206 1.0000
16.250 1.1336 0.08785 0.08275 0.0176 0.0204 1.0000
16.500 1.1170 0.09351 0.08865 0.0162 0.0204 1.0000
16.750 1.0989 0.09973 0.09510 0.0143 0.0203 1.0000
17.000 1.0793 0.10656 0.10215 0.0116 0.0204 1.0000
17.250 1.0584 0.11402 0.10982 0.0082 0.0206 1.0000
17.500 1.0366 0.12214 0.11814 0.0040 0.0208 1.0000
17.750 1.0142 0.13098 0.12714 -0.0009 0.0211 1.0000
18.000 0.9915 0.14055 0.13685 -0.0065 0.0215 1.0000
18.250 0.9692 0.15053 0.14692 -0.0119 0.0220 1.0000
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Polar data table (+)
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