AH 88-K-130/20 (ah88k130-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 88-K-130/20 (ah88k130-il) Reynolds number: 500,000 Max Cl/Cd: 121.17 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah88k130-il-500000.txt Download as CSV file: xf-ah88k130-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 88-K-130/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0622 0.08666 0.08376 -0.1081 0.8600 0.0163
-10.750 -0.0615 0.08269 0.07981 -0.1101 0.8592 0.0174
-10.500 -0.0595 0.07898 0.07611 -0.1118 0.8583 0.0177
-10.250 -0.0575 0.07528 0.07242 -0.1135 0.8574 0.0180
-10.000 -0.0554 0.07159 0.06875 -0.1152 0.8561 0.0182
-9.750 -0.0543 0.06771 0.06489 -0.1168 0.8549 0.0183
-9.500 -0.0549 0.06348 0.06066 -0.1188 0.8536 0.0184
-9.250 -0.0558 0.05919 0.05639 -0.1208 0.8523 0.0184
-9.000 -0.0578 0.05474 0.05195 -0.1231 0.8506 0.0184
-8.750 -0.0645 0.04910 0.04629 -0.1278 0.8488 0.0184
-8.500 -0.0746 0.04479 0.04192 -0.1306 0.8469 0.0184
-8.250 -0.0881 0.04138 0.03848 -0.1314 0.8448 0.0184
-8.000 -0.1042 0.03878 0.03583 -0.1301 0.8423 0.0185
-7.750 -0.1125 0.03571 0.03265 -0.1291 0.8401 0.0185
-7.500 -0.1162 0.03253 0.02934 -0.1280 0.8381 0.0185
-7.250 -0.1373 0.02529 0.02187 -0.1265 0.8359 0.0191
-7.000 -0.1424 0.03688 0.03300 -0.1330 0.8374 0.0196
-6.750 -0.1294 0.03475 0.03077 -0.1324 0.8359 0.0201
-6.500 -0.1144 0.03297 0.02886 -0.1319 0.8342 0.0210
-6.250 -0.0986 0.03108 0.02679 -0.1311 0.8324 0.0220
-6.000 -0.0808 0.02934 0.02486 -0.1303 0.8303 0.0240
-5.750 -0.0533 0.03000 0.02526 -0.1293 0.8282 0.0274
-5.500 -0.0337 0.02833 0.02332 -0.1284 0.8261 0.0276
-5.250 -0.0217 0.02292 0.01748 -0.1274 0.8241 0.0294
-5.000 0.0034 0.01854 0.01262 -0.1255 0.8225 0.0165
-4.750 0.0284 0.01666 0.01047 -0.1249 0.8210 0.0156
-4.500 0.0540 0.01548 0.00912 -0.1244 0.8195 0.0157
-4.250 0.0782 0.01463 0.00821 -0.1238 0.8176 0.0163
-4.000 0.1027 0.01403 0.00754 -0.1234 0.8155 0.0174
-3.750 0.1279 0.01352 0.00697 -0.1231 0.8132 0.0188
-3.500 0.1519 0.01266 0.00607 -0.1227 0.8111 0.0224
-3.250 0.1785 0.01224 0.00559 -0.1227 0.8093 0.0297
-3.000 0.2058 0.01192 0.00522 -0.1229 0.8077 0.0384
-2.750 0.2337 0.01169 0.00497 -0.1231 0.8062 0.0496
-2.500 0.2586 0.01103 0.00477 -0.1233 0.8040 0.1726
-2.250 0.2816 0.00948 0.00459 -0.1241 0.8013 0.5757
-2.000 0.3067 0.00913 0.00469 -0.1237 0.7988 0.7074
-1.750 0.3325 0.00923 0.00488 -0.1231 0.7966 0.7592
-1.500 0.3607 0.00937 0.00497 -0.1231 0.7948 0.7868
-1.250 0.3887 0.00950 0.00504 -0.1230 0.7931 0.8021
-1.000 0.4147 0.00979 0.00529 -0.1223 0.7914 0.8234
-0.750 0.4343 0.01003 0.00560 -0.1202 0.7879 0.8395
-0.500 0.4583 0.01017 0.00574 -0.1193 0.7849 0.8504
-0.250 0.4827 0.01019 0.00575 -0.1184 0.7825 0.8560
0.000 0.5101 0.01021 0.00573 -0.1183 0.7805 0.8624
0.250 0.5365 0.01022 0.00571 -0.1179 0.7787 0.8680
0.500 0.5611 0.01028 0.00578 -0.1173 0.7762 0.8735
0.750 0.5874 0.01032 0.00583 -0.1173 0.7725 0.8789
1.000 0.6130 0.01025 0.00577 -0.1169 0.7695 0.8817
1.250 0.6407 0.01019 0.00569 -0.1170 0.7671 0.8849
1.500 0.6702 0.01014 0.00562 -0.1176 0.7652 0.8881
1.750 0.6999 0.01014 0.00561 -0.1183 0.7625 0.8911
2.000 0.7240 0.01001 0.00553 -0.1177 0.7570 0.8938
2.250 0.7522 0.00975 0.00525 -0.1177 0.7526 0.8963
2.500 0.7818 0.00959 0.00506 -0.1181 0.7491 0.8990
2.750 0.8067 0.00953 0.00508 -0.1178 0.7434 0.9020
3.000 0.8364 0.00940 0.00496 -0.1184 0.7392 0.9043
3.250 0.8641 0.00923 0.00479 -0.1185 0.7354 0.9064
3.500 0.8868 0.00912 0.00476 -0.1176 0.7282 0.9091
3.750 0.9145 0.00893 0.00460 -0.1176 0.7229 0.9118
4.000 0.9386 0.00878 0.00451 -0.1169 0.7125 0.9148
4.250 0.9648 0.00863 0.00438 -0.1168 0.7000 0.9172
4.500 0.9897 0.00856 0.00433 -0.1163 0.6885 0.9193
4.750 1.0132 0.00853 0.00432 -0.1155 0.6757 0.9215
5.000 1.0349 0.00857 0.00431 -0.1144 0.6566 0.9244
5.250 1.0554 0.00871 0.00440 -0.1131 0.6337 0.9277
5.500 1.0753 0.00894 0.00456 -0.1117 0.6085 0.9308
5.750 1.0912 0.00922 0.00475 -0.1096 0.5781 0.9334
6.000 1.1034 0.00958 0.00503 -0.1068 0.5448 0.9363
6.250 1.1081 0.01011 0.00538 -0.1026 0.4967 0.9406
6.500 1.0978 0.01096 0.00595 -0.0957 0.4348 0.9471
6.750 1.0853 0.01205 0.00676 -0.0888 0.3748 0.9562
7.000 1.0768 0.01336 0.00777 -0.0833 0.3100 0.9681
7.250 1.0760 0.01499 0.00901 -0.0801 0.2350 1.0000
7.500 1.0774 0.01667 0.01032 -0.0774 0.1657 1.0000
7.750 1.0802 0.01834 0.01163 -0.0750 0.1023 1.0000
8.000 1.0867 0.01982 0.01286 -0.0730 0.0597 1.0000
8.250 1.0971 0.02108 0.01400 -0.0715 0.0364 1.0000
8.500 1.1087 0.02229 0.01521 -0.0700 0.0245 1.0000
8.750 1.1202 0.02351 0.01645 -0.0685 0.0189 1.0000
9.000 1.1354 0.02448 0.01747 -0.0675 0.0166 1.0000
9.250 1.1473 0.02568 0.01870 -0.0662 0.0147 1.0000
9.500 1.1505 0.02758 0.02072 -0.0638 0.0131 1.0000
9.750 1.1627 0.02879 0.02201 -0.0626 0.0123 1.0000
10.000 1.1761 0.02991 0.02319 -0.0616 0.0111 1.0000
10.250 1.1853 0.03141 0.02476 -0.0601 0.0104 1.0000
10.500 1.1939 0.03297 0.02642 -0.0586 0.0098 1.0000
10.750 1.2005 0.03478 0.02830 -0.0570 0.0092 1.0000
11.000 1.2044 0.03705 0.03069 -0.0549 0.0087 1.0000
11.250 1.2155 0.03941 0.03321 -0.0532 0.0083 1.0000
11.500 1.2306 0.04086 0.03478 -0.0523 0.0081 1.0000
11.750 1.2459 0.04246 0.03653 -0.0514 0.0078 1.0000
12.000 1.2636 0.04448 0.03873 -0.0505 0.0078 1.0000
12.250 1.2800 0.04698 0.04147 -0.0496 0.0077 1.0000
12.500 1.2909 0.04987 0.04462 -0.0485 0.0077 1.0000
12.750 1.2960 0.05297 0.04798 -0.0471 0.0077 1.0000
13.000 1.2964 0.05622 0.05147 -0.0456 0.0076 1.0000
13.250 1.2947 0.05919 0.05465 -0.0443 0.0073 1.0000
13.500 1.2878 0.06324 0.05899 -0.0430 0.0073 1.0000
13.750 1.2786 0.06741 0.06340 -0.0418 0.0073 1.0000
14.000 1.2634 0.07260 0.06885 -0.0410 0.0074 1.0000
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