AH 93-K-132/15 (ah93k132-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-K-132/15 (ah93k132-il) Reynolds number: 500,000 Max Cl/Cd: 114.65 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93k132-il-500000.txt Download as CSV file: xf-ah93k132-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2714 0.10015 0.09782 -0.0398 0.8102 0.0181
-10.000 -0.2747 0.09554 0.09321 -0.0422 0.8097 0.0184
-9.750 -0.2770 0.09118 0.08885 -0.0440 0.8090 0.0185
-9.500 -0.2777 0.08595 0.08365 -0.0472 0.8076 0.0185
-9.250 -0.2803 0.08066 0.07838 -0.0503 0.8063 0.0185
-9.000 -0.2847 0.07498 0.07273 -0.0538 0.8051 0.0186
-8.750 -0.2920 0.06852 0.06628 -0.0589 0.8039 0.0186
-8.500 -0.3837 0.07640 0.07403 -0.0561 0.8057 0.0183
-8.250 -0.3889 0.07103 0.06859 -0.0596 0.8037 0.0184
-8.000 -0.3532 0.04958 0.04707 -0.0661 0.7990 0.0188
-7.750 -0.3638 0.04495 0.04234 -0.0649 0.7979 0.0192
-7.500 -0.3624 0.04212 0.03945 -0.0636 0.7968 0.0195
-7.250 -0.3601 0.03916 0.03639 -0.0621 0.7959 0.0198
-7.000 -0.3555 0.03637 0.03348 -0.0606 0.7949 0.0202
-6.750 -0.3414 0.03285 0.02984 -0.0618 0.7910 0.0209
-6.500 -0.3305 0.02971 0.02654 -0.0610 0.7885 0.0223
-6.250 -0.3130 0.02829 0.02467 -0.0588 0.7864 0.0250
-6.000 -0.3032 0.02554 0.02162 -0.0566 0.7849 0.0251
-5.750 -0.3057 0.01910 0.01497 -0.0541 0.7837 0.0266
-5.000 -0.2763 0.02292 0.01685 -0.0451 0.7830 0.0148
-4.750 -0.2526 0.02131 0.01500 -0.0439 0.7822 0.0146
-4.500 -0.2287 0.02031 0.01389 -0.0429 0.7814 0.0151
-4.250 -0.1998 0.01972 0.01325 -0.0439 0.7775 0.0159
-4.000 -0.1731 0.01908 0.01254 -0.0439 0.7744 0.0169
-3.750 -0.1477 0.01850 0.01188 -0.0434 0.7725 0.0180
-3.500 -0.1246 0.01766 0.01098 -0.0424 0.7710 0.0198
-3.250 -0.0999 0.01724 0.01056 -0.0418 0.7700 0.0225
-3.000 -0.0750 0.01681 0.01006 -0.0410 0.7691 0.0248
-2.750 -0.0517 0.01615 0.00936 -0.0399 0.7682 0.0294
-2.500 -0.0270 0.01572 0.00891 -0.0391 0.7675 0.0382
-2.250 0.0004 0.01559 0.00894 -0.0400 0.7615 0.0695
-1.750 0.0422 0.01397 0.00846 -0.0381 0.7576 0.3736
-1.500 0.0522 0.01257 0.00812 -0.0347 0.7563 0.6590
-1.250 0.1017 0.01223 0.00858 -0.0378 0.7560 0.9069
-1.000 0.1344 0.01246 0.00875 -0.0381 0.7553 0.9337
-0.750 0.1730 0.01260 0.00880 -0.0398 0.7547 0.9468
-0.500 0.2190 0.01285 0.00896 -0.0429 0.7543 0.9614
-0.250 0.2671 0.01281 0.00885 -0.0469 0.7538 0.9672
0.000 0.3046 0.01319 0.00921 -0.0496 0.7487 0.9744
0.250 0.3516 0.01305 0.00901 -0.0537 0.7469 0.9773
0.500 0.3942 0.01291 0.00884 -0.0568 0.7456 0.9843
0.750 0.4450 0.01259 0.00848 -0.0616 0.7446 0.9896
1.000 0.4846 0.01230 0.00815 -0.0642 0.7435 0.9945
1.250 0.5232 0.01191 0.00773 -0.0665 0.7425 0.9971
1.500 0.5586 0.01154 0.00733 -0.0682 0.7416 0.9995
1.750 0.5846 0.01119 0.00696 -0.0678 0.7406 1.0000
2.000 0.6118 0.01117 0.00697 -0.0683 0.7358 1.0000
2.250 0.6373 0.01094 0.00674 -0.0680 0.7322 1.0000
2.500 0.6615 0.01059 0.00638 -0.0672 0.7300 1.0000
2.750 0.6858 0.01023 0.00600 -0.0664 0.7282 1.0000
3.000 0.7100 0.00989 0.00565 -0.0656 0.7266 1.0000
3.250 0.7381 0.00991 0.00574 -0.0663 0.7201 1.0000
3.500 0.7634 0.00963 0.00546 -0.0658 0.7165 1.0000
3.750 0.7881 0.00929 0.00510 -0.0651 0.7137 1.0000
4.000 0.8156 0.00927 0.00516 -0.0654 0.7066 1.0000
4.250 0.8411 0.00900 0.00489 -0.0650 0.7013 1.0000
4.500 0.8679 0.00891 0.00483 -0.0650 0.6926 1.0000
4.750 0.8933 0.00869 0.00459 -0.0645 0.6854 1.0000
5.000 0.9198 0.00861 0.00454 -0.0645 0.6733 1.0000
5.250 0.9458 0.00855 0.00445 -0.0643 0.6571 1.0000
5.500 0.9722 0.00860 0.00448 -0.0643 0.6391 1.0000
5.750 0.9981 0.00871 0.00454 -0.0642 0.6184 1.0000
6.000 1.0238 0.00893 0.00469 -0.0643 0.5934 1.0000
6.250 1.0488 0.00926 0.00493 -0.0643 0.5659 1.0000
6.500 1.0726 0.00972 0.00527 -0.0642 0.5346 1.0000
6.750 1.0946 0.01031 0.00575 -0.0640 0.5010 1.0000
7.000 1.1142 0.01099 0.00630 -0.0635 0.4655 1.0000
7.250 1.1287 0.01194 0.00706 -0.0623 0.4220 1.0000
7.500 1.1361 0.01315 0.00805 -0.0602 0.3750 1.0000
7.750 1.1347 0.01435 0.00905 -0.0565 0.3366 1.0000
8.000 1.1221 0.01526 0.00984 -0.0500 0.3108 1.0000
8.250 1.1117 0.01612 0.01056 -0.0438 0.2844 1.0000
8.500 1.1059 0.01704 0.01134 -0.0387 0.2544 1.0000
8.750 1.1020 0.01803 0.01216 -0.0342 0.2230 1.0000
9.000 1.1010 0.01903 0.01299 -0.0302 0.1900 1.0000
9.250 1.1012 0.02006 0.01385 -0.0266 0.1593 1.0000
9.500 1.1030 0.02112 0.01475 -0.0234 0.1306 1.0000
9.750 1.1071 0.02217 0.01567 -0.0206 0.1060 1.0000
10.250 1.1205 0.02429 0.01760 -0.0162 0.0699 1.0000
10.500 1.1286 0.02537 0.01864 -0.0143 0.0558 1.0000
10.750 1.1363 0.02654 0.01975 -0.0125 0.0440 1.0000
11.000 1.1443 0.02775 0.02094 -0.0108 0.0349 1.0000
11.250 1.1503 0.02913 0.02231 -0.0090 0.0285 1.0000
11.500 1.1595 0.03037 0.02358 -0.0076 0.0247 1.0000
11.750 1.1634 0.03209 0.02535 -0.0058 0.0216 1.0000
12.000 1.1745 0.03328 0.02661 -0.0048 0.0197 1.0000
12.250 1.1833 0.03468 0.02805 -0.0037 0.0179 1.0000
12.500 1.1833 0.03686 0.03030 -0.0019 0.0163 1.0000
12.750 1.1898 0.03856 0.03211 -0.0007 0.0155 1.0000
13.000 1.1978 0.04017 0.03381 0.0002 0.0146 1.0000
13.250 1.2046 0.04192 0.03565 0.0011 0.0138 1.0000
13.500 1.2110 0.04375 0.03754 0.0020 0.0130 1.0000
13.750 1.2136 0.04596 0.03981 0.0029 0.0123 1.0000
14.000 1.2061 0.04915 0.04311 0.0045 0.0116 1.0000
14.250 1.2135 0.05105 0.04511 0.0050 0.0112 1.0000
14.500 1.2197 0.05308 0.04725 0.0055 0.0107 1.0000
14.750 1.2237 0.05537 0.04964 0.0060 0.0102 1.0000
15.000 1.2269 0.05779 0.05217 0.0065 0.0098 1.0000
15.250 1.2298 0.06030 0.05479 0.0068 0.0095 1.0000
15.500 1.2319 0.06296 0.05753 0.0070 0.0091 1.0000
15.750 1.2324 0.06581 0.06046 0.0072 0.0089 1.0000
16.000 1.2306 0.06893 0.06368 0.0074 0.0086 1.0000
16.250 1.2253 0.07241 0.06728 0.0080 0.0083 1.0000
16.500 1.2180 0.07617 0.07122 0.0087 0.0081 1.0000
16.750 1.2167 0.07964 0.07484 0.0082 0.0080 1.0000
17.000 1.2138 0.08337 0.07873 0.0076 0.0079 1.0000
17.250 1.2094 0.08740 0.08292 0.0069 0.0078 1.0000
17.500 1.2036 0.09175 0.08743 0.0059 0.0076 1.0000
17.750 1.1960 0.09642 0.09227 0.0047 0.0075 1.0000
18.000 1.1870 0.10147 0.09749 0.0031 0.0075 1.0000
18.250 1.1766 0.10691 0.10311 0.0012 0.0074 1.0000
18.500 1.1648 0.11276 0.10913 -0.0011 0.0073 1.0000
18.750 1.1519 0.11902 0.11557 -0.0038 0.0073 1.0000
19.000 1.1375 0.12575 0.12247 -0.0070 0.0073 1.0000
19.250 1.1222 0.13295 0.12984 -0.0106 0.0073 1.0000
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