AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: AH-6-40-7 AIRFOIL (ah6407-il) Reynolds number: 50,000 Max Cl/Cd: 46.93 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah6407-il-50000-n5.txt Download as CSV file: xf-ah6407-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH-6-40-7 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3207 0.10272 0.09642 -0.0230 1.0000 0.0855
-6.750 -0.3246 0.10148 0.09528 -0.0237 1.0000 0.0886
-6.500 -0.3267 0.10091 0.09481 -0.0277 1.0000 0.0902
-6.000 -0.3203 0.09412 0.08816 -0.0258 1.0000 0.0926
-5.750 -0.3163 0.09112 0.08520 -0.0241 1.0000 0.0950
-5.500 -0.3108 0.08850 0.08262 -0.0245 1.0000 0.0980
-5.250 -0.2986 0.08622 0.08036 -0.0296 1.0000 0.1037
-5.000 -0.2754 0.08320 0.07729 -0.0388 1.0000 0.1058
-4.750 -0.2757 0.07957 0.07374 -0.0337 1.0000 0.1081
-4.500 -0.2652 0.07677 0.07095 -0.0337 1.0000 0.1143
-4.000 -0.2253 0.07011 0.06424 -0.0412 1.0000 0.1260
-3.750 -0.1691 0.06195 0.05573 -0.0551 1.0000 0.0722
-3.500 -0.0925 0.05338 0.04653 -0.0735 1.0000 0.0629
-3.250 -0.0689 0.05148 0.04474 -0.0744 0.9958 0.0693
-3.000 -0.0051 0.04546 0.03819 -0.0861 0.9932 0.0674
-2.750 0.0517 0.04108 0.03328 -0.0950 0.9902 0.0720
-2.500 0.1131 0.03647 0.02778 -0.1039 0.9884 0.0750
-2.250 0.1651 0.03336 0.02392 -0.1099 0.9859 0.0780
-2.000 0.2065 0.03212 0.02238 -0.1134 0.9808 0.0865
-1.750 0.2532 0.03024 0.01982 -0.1174 0.9769 0.0890
-1.500 0.2964 0.02896 0.01810 -0.1206 0.9715 0.0923
-1.250 0.3372 0.02813 0.01699 -0.1233 0.9648 0.0976
-1.000 0.3796 0.02744 0.01597 -0.1261 0.9579 0.1076
-0.750 0.4218 0.02694 0.01539 -0.1290 0.9496 0.1272
-0.500 0.4618 0.02633 0.01472 -0.1312 0.9399 0.1525
-0.250 0.5018 0.02572 0.01431 -0.1336 0.9298 0.2268
0.000 0.5417 0.02494 0.01414 -0.1363 0.9198 0.3841
0.250 0.5693 0.02341 0.01371 -0.1356 0.9079 1.0000
0.500 0.6122 0.02334 0.01324 -0.1381 0.8978 1.0000
0.750 0.6469 0.02333 0.01299 -0.1390 0.8845 1.0000
1.000 0.6806 0.02328 0.01276 -0.1397 0.8710 1.0000
1.250 0.7137 0.02320 0.01255 -0.1401 0.8571 1.0000
1.500 0.7463 0.02309 0.01234 -0.1404 0.8427 1.0000
1.750 0.7784 0.02296 0.01212 -0.1405 0.8276 1.0000
2.000 0.8101 0.02280 0.01193 -0.1404 0.8118 1.0000
2.250 0.8410 0.02264 0.01173 -0.1402 0.7948 1.0000
2.500 0.8682 0.02262 0.01169 -0.1394 0.7744 1.0000
2.750 0.8982 0.02248 0.01157 -0.1389 0.7547 1.0000
3.000 0.9267 0.02243 0.01150 -0.1382 0.7324 1.0000
3.250 0.9562 0.02235 0.01140 -0.1376 0.7092 1.0000
3.500 0.9837 0.02240 0.01144 -0.1368 0.6830 1.0000
3.750 1.0116 0.02249 0.01152 -0.1361 0.6562 1.0000
4.000 1.0389 0.02265 0.01163 -0.1353 0.6283 1.0000
4.250 1.0656 0.02292 0.01184 -0.1344 0.6006 1.0000
4.500 1.0917 0.02329 0.01216 -0.1336 0.5741 1.0000
4.750 1.1165 0.02379 0.01263 -0.1327 0.5483 1.0000
5.000 1.1416 0.02434 0.01316 -0.1319 0.5254 1.0000
5.250 1.1664 0.02496 0.01378 -0.1311 0.5044 1.0000
5.500 1.1916 0.02561 0.01447 -0.1305 0.4859 1.0000
5.750 1.2169 0.02632 0.01523 -0.1299 0.4689 1.0000
6.000 1.2421 0.02706 0.01607 -0.1294 0.4534 1.0000
6.250 1.2674 0.02783 0.01696 -0.1288 0.4390 1.0000
6.500 1.2926 0.02863 0.01796 -0.1283 0.4255 1.0000
6.750 1.3169 0.02949 0.01903 -0.1277 0.4122 1.0000
7.000 1.3402 0.03036 0.02010 -0.1269 0.3983 1.0000
7.250 1.3623 0.03122 0.02118 -0.1258 0.3836 1.0000
7.500 1.3835 0.03209 0.02228 -0.1246 0.3686 1.0000
7.750 1.4036 0.03295 0.02345 -0.1232 0.3529 1.0000
8.000 1.4165 0.03367 0.02439 -0.1207 0.3300 1.0000
8.250 1.4185 0.03428 0.02504 -0.1166 0.2954 1.0000
8.500 1.4165 0.03522 0.02595 -0.1123 0.2536 1.0000
8.750 1.4177 0.03649 0.02724 -0.1087 0.2096 1.0000
9.000 1.4150 0.03844 0.02893 -0.1049 0.1408 1.0000
9.250 1.4035 0.04158 0.03150 -0.1005 0.0938 1.0000
9.500 1.3951 0.04497 0.03471 -0.0969 0.0711 1.0000
9.750 1.3879 0.04825 0.03800 -0.0938 0.0606 1.0000
10.000 1.3787 0.05175 0.04155 -0.0911 0.0544 1.0000
10.250 1.3723 0.05513 0.04511 -0.0889 0.0497 1.0000
10.500 1.3653 0.05872 0.04889 -0.0872 0.0464 1.0000
10.750 1.3569 0.06263 0.05296 -0.0859 0.0443 1.0000
11.000 1.3473 0.06685 0.05730 -0.0849 0.0427 1.0000
11.250 1.3423 0.07072 0.06139 -0.0841 0.0409 1.0000
11.500 1.3386 0.07456 0.06556 -0.0834 0.0388 1.0000
11.750 1.3345 0.07853 0.06973 -0.0830 0.0369 1.0000
12.000 1.3300 0.08261 0.07395 -0.0829 0.0353 1.0000
12.250 1.3258 0.08664 0.07806 -0.0828 0.0339 1.0000
12.500 1.3260 0.09022 0.08181 -0.0820 0.0327 1.0000
12.750 1.3277 0.09387 0.08577 -0.0813 0.0319 1.0000
13.000 1.3271 0.09803 0.09024 -0.0811 0.0312 1.0000
13.250 1.3231 0.10285 0.09535 -0.0818 0.0307 1.0000
13.500 1.3160 0.10831 0.10110 -0.0833 0.0303 1.0000
13.750 1.3067 0.11438 0.10744 -0.0856 0.0300 1.0000
14.000 1.2958 0.12106 0.11437 -0.0888 0.0298 1.0000
14.250 1.2836 0.12840 0.12195 -0.0927 0.0298 1.0000
14.500 1.2703 0.13649 0.13027 -0.0975 0.0299 1.0000
14.750 1.2563 0.14532 0.13930 -0.1030 0.0302 1.0000
15.000 1.2421 0.15482 0.14897 -0.1091 0.0307 1.0000
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Polar data table (+)
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