AH 93-K-130/15 (ah93k130-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-130/15 (ah93k130-il) Reynolds number: 100,000 Max Cl/Cd: 40.7 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k130-il-100000-n5.txt Download as CSV file: xf-ah93k130-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-130/15
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3375 0.08625 0.08132 -0.0693 0.8574 0.0308
-9.000 -0.3355 0.08157 0.07664 -0.0734 0.8557 0.0304
-8.750 -0.3365 0.07691 0.07196 -0.0770 0.8535 0.0302
-8.500 -0.3429 0.07282 0.06780 -0.0787 0.8512 0.0300
-8.250 -0.3492 0.06845 0.06330 -0.0799 0.8491 0.0300
-8.000 -0.3547 0.06410 0.05875 -0.0801 0.8469 0.0302
-7.750 -0.3594 0.05999 0.05433 -0.0791 0.8448 0.0306
-7.250 -0.3568 0.05256 0.04632 -0.0772 0.8394 0.0314
-7.000 -0.3521 0.04945 0.04289 -0.0753 0.8367 0.0315
-6.750 -0.3455 0.04662 0.03972 -0.0731 0.8343 0.0316
-6.500 -0.3365 0.04416 0.03693 -0.0708 0.8323 0.0320
-6.250 -0.3250 0.04203 0.03451 -0.0693 0.8290 0.0325
-6.000 -0.3119 0.04017 0.03234 -0.0676 0.8256 0.0331
-5.750 -0.2961 0.03875 0.03067 -0.0660 0.8229 0.0344
-5.500 -0.2788 0.03744 0.02905 -0.0644 0.8207 0.0366
-5.250 -0.2604 0.03586 0.02704 -0.0626 0.8186 0.0386
-5.000 -0.2432 0.03442 0.02522 -0.0612 0.8143 0.0396
-4.750 -0.2222 0.03318 0.02360 -0.0599 0.8111 0.0408
-4.500 -0.1998 0.03184 0.02214 -0.0592 0.8086 0.0432
-4.250 -0.1761 0.03115 0.02134 -0.0585 0.8066 0.0466
-4.000 -0.1523 0.03034 0.02035 -0.0579 0.8040 0.0493
-3.750 -0.1322 0.02970 0.01958 -0.0569 0.7993 0.0515
-3.500 -0.1095 0.02899 0.01881 -0.0561 0.7962 0.0552
-3.250 -0.0860 0.02847 0.01828 -0.0554 0.7938 0.0602
-3.000 -0.0616 0.02794 0.01765 -0.0545 0.7919 0.0646
-2.750 -0.0470 0.02770 0.01739 -0.0528 0.7861 0.0686
-2.500 -0.0265 0.02743 0.01710 -0.0517 0.7824 0.0775
-2.250 -0.0032 0.02705 0.01671 -0.0508 0.7798 0.0887
-2.000 0.0219 0.02664 0.01632 -0.0502 0.7779 0.1104
-1.750 0.1499 0.02402 0.01669 -0.0699 0.7803 0.8750
-1.500 0.2880 0.02464 0.01695 -0.0906 0.7831 0.9982
-1.250 0.3144 0.02468 0.01681 -0.0908 0.7802 1.0000
-1.000 0.3356 0.02471 0.01670 -0.0896 0.7778 1.0000
-0.750 0.3522 0.02513 0.01704 -0.0888 0.7712 1.0000
-0.500 0.3724 0.02525 0.01705 -0.0878 0.7673 1.0000
-0.250 0.3943 0.02527 0.01696 -0.0867 0.7646 1.0000
0.000 0.4097 0.02569 0.01733 -0.0854 0.7581 1.0000
0.250 0.4293 0.02584 0.01741 -0.0843 0.7538 1.0000
0.500 0.4521 0.02583 0.01732 -0.0833 0.7510 1.0000
0.750 0.4655 0.02630 0.01776 -0.0816 0.7439 1.0000
1.000 0.4860 0.02639 0.01780 -0.0805 0.7396 1.0000
1.250 0.5101 0.02631 0.01766 -0.0796 0.7370 1.0000
1.500 0.5202 0.02687 0.01822 -0.0775 0.7284 1.0000
1.750 0.5433 0.02684 0.01815 -0.0765 0.7249 1.0000
2.250 0.5763 0.02732 0.01861 -0.0732 0.7128 1.0000
2.500 0.6019 0.02715 0.01844 -0.0725 0.7101 1.0000
2.750 0.6099 0.02773 0.01903 -0.0699 0.7007 1.0000
3.000 0.6350 0.02756 0.01887 -0.0692 0.6974 1.0000
3.500 0.6685 0.02791 0.01927 -0.0657 0.6845 1.0000
3.750 0.6948 0.02765 0.01904 -0.0651 0.6814 1.0000
4.000 0.7026 0.02819 0.01961 -0.0623 0.6716 1.0000
4.250 0.7309 0.02781 0.01928 -0.0619 0.6689 1.0000
4.500 0.7372 0.02841 0.01994 -0.0588 0.6588 1.0000
4.750 0.7653 0.02800 0.01959 -0.0584 0.6557 1.0000
5.000 0.7726 0.02849 0.02012 -0.0553 0.6458 1.0000
5.250 0.8002 0.02804 0.01975 -0.0548 0.6421 1.0000
5.750 0.8358 0.02785 0.01972 -0.0509 0.6282 1.0000
6.000 0.8459 0.02804 0.01998 -0.0480 0.6184 1.0000
6.250 0.8771 0.02730 0.01934 -0.0477 0.6133 1.0000
6.500 0.8880 0.02747 0.01958 -0.0449 0.6022 1.0000
6.750 0.9124 0.02703 0.01927 -0.0437 0.5939 1.0000
7.000 0.9388 0.02646 0.01880 -0.0427 0.5842 1.0000
7.250 0.9573 0.02625 0.01867 -0.0407 0.5706 1.0000
7.500 0.9822 0.02571 0.01819 -0.0395 0.5548 1.0000
7.750 0.9969 0.02573 0.01828 -0.0371 0.5350 1.0000
8.000 1.0178 0.02546 0.01803 -0.0353 0.5129 1.0000
8.250 1.0322 0.02558 0.01815 -0.0329 0.4870 1.0000
8.500 1.0468 0.02572 0.01820 -0.0306 0.4552 1.0000
8.750 1.0568 0.02615 0.01849 -0.0277 0.4182 1.0000
9.000 1.0624 0.02689 0.01905 -0.0246 0.3777 1.0000
9.250 1.0640 0.02794 0.01987 -0.0212 0.3357 1.0000
9.500 1.0633 0.02926 0.02096 -0.0179 0.2929 1.0000
9.750 1.0610 0.03080 0.02224 -0.0146 0.2499 1.0000
10.000 1.0584 0.03249 0.02368 -0.0116 0.2090 1.0000
10.250 1.0570 0.03424 0.02521 -0.0089 0.1724 1.0000
10.500 1.0563 0.03605 0.02682 -0.0065 0.1399 1.0000
10.750 1.0568 0.03786 0.02849 -0.0043 0.1139 1.0000
11.000 1.0578 0.03971 0.03022 -0.0022 0.0949 1.0000
11.250 1.0598 0.04153 0.03202 -0.0003 0.0802 1.0000
11.500 1.0613 0.04347 0.03392 0.0015 0.0700 1.0000
11.750 1.0650 0.04532 0.03584 0.0031 0.0622 1.0000
12.000 1.0667 0.04739 0.03792 0.0046 0.0565 1.0000
12.250 1.0708 0.04929 0.03993 0.0059 0.0511 1.0000
12.500 1.0710 0.05160 0.04223 0.0073 0.0473 1.0000
12.750 1.0763 0.05351 0.04428 0.0085 0.0442 1.0000
13.000 1.0812 0.05549 0.04638 0.0097 0.0414 1.0000
13.250 1.0850 0.05761 0.04857 0.0107 0.0389 1.0000
13.500 1.0873 0.05989 0.05083 0.0118 0.0366 1.0000
13.750 1.0948 0.06178 0.05296 0.0128 0.0344 1.0000
14.000 1.1018 0.06375 0.05508 0.0137 0.0326 1.0000
14.250 1.1082 0.06582 0.05728 0.0146 0.0311 1.0000
14.500 1.1128 0.06809 0.05964 0.0153 0.0296 1.0000
14.750 1.1168 0.07047 0.06205 0.0160 0.0282 1.0000
15.000 1.1208 0.07304 0.06481 0.0167 0.0269 1.0000
15.250 1.1228 0.07590 0.06793 0.0171 0.0258 1.0000
15.500 1.1239 0.07897 0.07124 0.0176 0.0249 1.0000
15.750 1.1227 0.08238 0.07488 0.0178 0.0242 1.0000
16.000 1.1190 0.08615 0.07888 0.0177 0.0236 1.0000
16.250 1.1132 0.09024 0.08318 0.0172 0.0230 1.0000
16.500 1.1058 0.09460 0.08773 0.0163 0.0225 1.0000
16.750 1.0974 0.09919 0.09253 0.0151 0.0220 1.0000
17.000 1.0886 0.10399 0.09749 0.0136 0.0216 1.0000
17.250 1.0792 0.10903 0.10267 0.0118 0.0212 1.0000
17.500 1.0686 0.11445 0.10823 0.0097 0.0208 1.0000
17.750 1.0554 0.12059 0.11454 0.0070 0.0205 1.0000
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