AH 93-K-131/15 (ah93k131-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-K-131/15 (ah93k131-il) Reynolds number: 200,000 Max Cl/Cd: 76 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93k131-il-200000.txt Download as CSV file: xf-ah93k131-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-131/15
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3254 0.09259 0.08924 -0.0539 0.8591 0.0473
-8.750 -0.3203 0.08837 0.08504 -0.0582 0.8569 0.0487
-8.500 -0.3185 0.08357 0.08026 -0.0642 0.8547 0.0501
-8.250 -0.3220 0.07854 0.07520 -0.0705 0.8521 0.0515
-8.000 -0.3348 0.07458 0.07111 -0.0737 0.8494 0.0531
-7.750 -0.3435 0.07147 0.06763 -0.0767 0.8460 0.0544
-7.500 -0.3493 0.06546 0.06143 -0.0774 0.8435 0.0552
-7.250 -0.3354 0.06167 0.05777 -0.0775 0.8412 0.0565
-7.000 -0.3255 0.05955 0.05563 -0.0763 0.8389 0.0579
-6.750 -0.3178 0.05747 0.05346 -0.0749 0.8367 0.0599
-6.500 -0.3054 0.05502 0.05070 -0.0754 0.8332 0.0660
-6.250 -0.3051 0.05134 0.04667 -0.0736 0.8296 0.0698
-6.000 -0.2900 0.04945 0.04485 -0.0727 0.8271 0.0724
-5.750 -0.2784 0.04774 0.04297 -0.0706 0.8252 0.0765
-5.500 -0.2718 0.04546 0.04023 -0.0686 0.8209 0.0842
-5.250 -0.2559 0.04350 0.03828 -0.0678 0.8173 0.0871
-5.000 -0.2465 0.03604 0.02965 -0.0615 0.8145 0.0503
-4.750 -0.2290 0.03387 0.02706 -0.0591 0.8125 0.0498
-4.500 -0.2114 0.03245 0.02532 -0.0576 0.8080 0.0507
-4.250 -0.1911 0.03088 0.02343 -0.0563 0.8042 0.0506
-4.000 -0.1671 0.02961 0.02187 -0.0552 0.8016 0.0517
-3.750 -0.1418 0.02920 0.02119 -0.0541 0.7995 0.0543
-3.500 -0.1147 0.02745 0.01931 -0.0535 0.7981 0.0571
-3.250 -0.0968 0.02706 0.01893 -0.0531 0.7914 0.0595
-3.000 -0.0721 0.02658 0.01839 -0.0525 0.7882 0.0637
-2.750 -0.0457 0.02624 0.01794 -0.0518 0.7861 0.0679
-2.500 -0.0217 0.02531 0.01707 -0.0507 0.7845 0.0736
-2.250 -0.0075 0.02541 0.01718 -0.0495 0.7771 0.0794
-2.000 0.0143 0.02501 0.01681 -0.0484 0.7739 0.0901
-1.750 0.0381 0.02457 0.01640 -0.0472 0.7718 0.1092
-1.500 0.1753 0.02246 0.01733 -0.0676 0.7743 0.9607
-1.250 0.3206 0.02233 0.01689 -0.0904 0.7765 0.9981
-1.000 0.3493 0.02228 0.01673 -0.0909 0.7735 1.0000
-0.750 0.3697 0.02223 0.01658 -0.0893 0.7712 1.0000
-0.500 0.3909 0.02261 0.01691 -0.0893 0.7656 1.0000
-0.250 0.4119 0.02278 0.01702 -0.0886 0.7609 1.0000
0.000 0.4335 0.02271 0.01687 -0.0873 0.7581 1.0000
0.250 0.4552 0.02257 0.01666 -0.0857 0.7563 1.0000
0.500 0.4743 0.02323 0.01731 -0.0858 0.7481 1.0000
0.750 0.4964 0.02317 0.01720 -0.0847 0.7449 1.0000
1.000 0.5194 0.02298 0.01697 -0.0834 0.7429 1.0000
1.250 0.5424 0.02278 0.01672 -0.0819 0.7412 1.0000
1.500 0.5595 0.02356 0.01751 -0.0818 0.7316 1.0000
1.750 0.5834 0.02332 0.01725 -0.0806 0.7294 1.0000
2.000 0.6079 0.02298 0.01688 -0.0793 0.7278 1.0000
2.250 0.6236 0.02373 0.01766 -0.0786 0.7182 1.0000
2.500 0.6487 0.02337 0.01728 -0.0775 0.7158 1.0000
2.750 0.6746 0.02288 0.01679 -0.0764 0.7142 1.0000
3.000 0.6901 0.02358 0.01753 -0.0754 0.7047 1.0000
3.250 0.7160 0.02312 0.01707 -0.0744 0.7023 1.0000
3.500 0.7432 0.02248 0.01644 -0.0734 0.7007 1.0000
3.750 0.7704 0.02176 0.01574 -0.0722 0.6995 1.0000
4.000 0.7866 0.02244 0.01648 -0.0713 0.6891 1.0000
4.250 0.8143 0.02169 0.01576 -0.0704 0.6874 1.0000
4.500 0.8427 0.02084 0.01495 -0.0694 0.6861 1.0000
4.750 0.8714 0.01997 0.01411 -0.0684 0.6848 1.0000
5.000 0.8893 0.02038 0.01461 -0.0675 0.6744 1.0000
5.250 0.9191 0.01938 0.01365 -0.0666 0.6726 1.0000
5.500 0.9496 0.01827 0.01259 -0.0657 0.6708 1.0000
5.750 0.9699 0.01836 0.01278 -0.0648 0.6602 1.0000
6.000 1.0015 0.01707 0.01151 -0.0639 0.6571 1.0000
6.250 1.0247 0.01670 0.01124 -0.0628 0.6453 1.0000
6.500 1.0490 0.01627 0.01089 -0.0618 0.6339 1.0000
6.750 1.0741 0.01584 0.01052 -0.0608 0.6222 1.0000
7.000 1.0982 0.01552 0.01025 -0.0598 0.6073 1.0000
7.250 1.1216 0.01529 0.01005 -0.0587 0.5894 1.0000
7.500 1.1439 0.01519 0.00995 -0.0575 0.5684 1.0000
7.750 1.1635 0.01531 0.01003 -0.0560 0.5428 1.0000
8.000 1.1800 0.01565 0.01028 -0.0541 0.5127 1.0000
8.250 1.1912 0.01624 0.01077 -0.0517 0.4771 1.0000
8.500 1.1960 0.01710 0.01146 -0.0483 0.4387 1.0000
8.750 1.1924 0.01823 0.01242 -0.0440 0.4004 1.0000
9.000 1.1784 0.01933 0.01334 -0.0377 0.3697 1.0000
9.250 1.1657 0.02057 0.01438 -0.0319 0.3370 1.0000
9.500 1.1557 0.02196 0.01557 -0.0270 0.3013 1.0000
9.750 1.1460 0.02353 0.01691 -0.0224 0.2642 1.0000
10.000 1.1377 0.02521 0.01837 -0.0184 0.2254 1.0000
10.250 1.1299 0.02704 0.01995 -0.0147 0.1875 1.0000
10.500 1.1238 0.02893 0.02162 -0.0114 0.1524 1.0000
10.750 1.1193 0.03086 0.02335 -0.0085 0.1236 1.0000
11.000 1.1167 0.03277 0.02511 -0.0059 0.1008 1.0000
11.250 1.1145 0.03475 0.02697 -0.0035 0.0839 1.0000
11.500 1.1131 0.03680 0.02895 -0.0014 0.0703 1.0000
11.750 1.1137 0.03879 0.03092 0.0005 0.0593 1.0000
12.000 1.1154 0.04078 0.03294 0.0023 0.0507 1.0000
12.250 1.1138 0.04309 0.03523 0.0041 0.0447 1.0000
12.500 1.1184 0.04494 0.03715 0.0054 0.0394 1.0000
12.750 1.1161 0.04742 0.03959 0.0073 0.0360 1.0000
13.000 1.1230 0.04917 0.04147 0.0086 0.0332 1.0000
13.250 1.1287 0.05103 0.04339 0.0098 0.0308 1.0000
13.500 1.1335 0.05299 0.04534 0.0112 0.0287 1.0000
13.750 1.1422 0.05470 0.04716 0.0127 0.0269 1.0000
14.000 1.1500 0.05650 0.04911 0.0137 0.0253 1.0000
14.250 1.1582 0.05834 0.05105 0.0147 0.0240 1.0000
14.500 1.1664 0.06022 0.05303 0.0158 0.0231 1.0000
14.750 1.1747 0.06217 0.05505 0.0168 0.0222 1.0000
15.000 1.1857 0.06426 0.05723 0.0181 0.0215 1.0000
15.250 1.1941 0.06758 0.06079 0.0197 0.0209 1.0000
15.500 1.1908 0.07086 0.06432 0.0204 0.0208 1.0000
15.750 1.1850 0.07453 0.06825 0.0210 0.0207 1.0000
16.000 1.1764 0.07859 0.07255 0.0212 0.0206 1.0000
16.250 1.1652 0.08302 0.07723 0.0211 0.0205 1.0000
16.500 1.1520 0.08786 0.08231 0.0206 0.0205 1.0000
16.750 1.1368 0.09312 0.08780 0.0196 0.0204 1.0000
17.000 1.1202 0.09885 0.09375 0.0180 0.0204 1.0000
17.250 1.1024 0.10507 0.10019 0.0159 0.0204 1.0000
17.500 1.0836 0.11179 0.10712 0.0133 0.0205 1.0000
17.750 1.0638 0.11905 0.11456 0.0100 0.0206 1.0000
18.000 1.0436 0.12684 0.12252 0.0062 0.0208 1.0000
18.250 0.8082 0.12126 0.11754 0.0166 0.0233 1.0000
18.500 0.9711 0.15418 0.15048 -0.0112 0.0227 1.0000
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Polar data table (+)
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