AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH-7-47-6 AIRFOIL (ah7476-il) Reynolds number: 200,000 Max Cl/Cd: 103.13 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah7476-il-200000-n5.txt Download as CSV file: xf-ah7476-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH-7-47-6 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3364 0.12662 0.12302 -0.0247 1.0000 0.0173
-9.500 -0.3358 0.12435 0.12079 -0.0241 1.0000 0.0176
-9.250 -0.3356 0.12214 0.11861 -0.0234 1.0000 0.0180
-9.000 -0.3226 0.11856 0.11503 -0.0266 0.9981 0.0185
-8.750 -0.3096 0.11508 0.11155 -0.0302 0.9960 0.0188
-8.500 -0.2972 0.11171 0.10819 -0.0337 0.9936 0.0189
-8.250 -0.2861 0.10873 0.10522 -0.0379 0.9901 0.0191
-8.000 -0.2747 0.10582 0.10231 -0.0429 0.9868 0.0192
-7.750 -0.2641 0.10196 0.09848 -0.0443 0.9829 0.0193
-7.500 -0.2497 0.09795 0.09445 -0.0450 0.9809 0.0196
-7.250 -0.2344 0.09456 0.09105 -0.0479 0.9783 0.0200
-7.000 -0.2213 0.09141 0.08791 -0.0505 0.9731 0.0205
-6.750 -0.2013 0.08778 0.08428 -0.0551 0.9698 0.0212
-6.500 -0.1848 0.08452 0.08101 -0.0589 0.9646 0.0222
-6.250 -0.1520 0.08034 0.07680 -0.0699 0.9600 0.0236
-6.000 -0.1186 0.07587 0.07229 -0.0811 0.9536 0.0238
-5.500 -0.0765 0.06795 0.06436 -0.0869 0.9489 0.0244
-5.250 -0.0585 0.06512 0.06150 -0.0889 0.9436 0.0252
-5.000 -0.0275 0.06160 0.05794 -0.0950 0.9402 0.0269
-4.750 0.0584 0.05389 0.04998 -0.1198 0.9386 0.0298
-4.500 0.0768 0.05091 0.04702 -0.1202 0.9371 0.0306
-4.250 0.1010 0.04839 0.04447 -0.1226 0.9312 0.0319
-4.000 0.1767 0.04187 0.03765 -0.1400 0.9297 0.0378
-3.750 0.2075 0.03960 0.03535 -0.1429 0.9273 0.0396
-3.500 0.2755 0.03441 0.02978 -0.1558 0.9265 0.0472
-3.250 0.3103 0.03268 0.02804 -0.1589 0.9250 0.0507
-3.000 0.3489 0.03048 0.02568 -0.1631 0.9204 0.0609
-2.500 0.4602 0.02236 0.01648 -0.1771 0.9166 0.0435
-2.250 0.5040 0.02029 0.01404 -0.1809 0.9145 0.0424
-2.000 0.5475 0.01845 0.01177 -0.1843 0.9125 0.0400
-1.750 0.5824 0.01759 0.01050 -0.1853 0.9076 0.0375
-1.500 0.6147 0.01684 0.00960 -0.1862 0.9018 0.0369
-1.250 0.6526 0.01581 0.00841 -0.1883 0.8981 0.0366
-1.000 0.6837 0.01517 0.00767 -0.1889 0.8916 0.0365
-0.750 0.7166 0.01460 0.00703 -0.1899 0.8864 0.0366
-0.500 0.7523 0.01407 0.00646 -0.1915 0.8828 0.0372
-0.250 0.7833 0.01348 0.00593 -0.1923 0.8763 0.0393
0.000 0.8168 0.01308 0.00555 -0.1934 0.8703 0.0396
0.250 0.8506 0.01275 0.00523 -0.1946 0.8640 0.0396
0.500 0.8821 0.01252 0.00501 -0.1952 0.8559 0.0397
0.750 0.9147 0.01231 0.00479 -0.1961 0.8486 0.0400
1.000 0.9457 0.01217 0.00464 -0.1966 0.8394 0.0406
1.250 0.9760 0.01208 0.00453 -0.1969 0.8291 0.0414
1.500 1.0068 0.01200 0.00443 -0.1974 0.8182 0.0427
1.750 1.0367 0.01196 0.00438 -0.1976 0.8052 0.0447
2.000 1.0641 0.01196 0.00440 -0.1972 0.7853 0.0536
2.250 1.0867 0.01062 0.00463 -0.1961 0.7587 1.0000
2.500 1.1117 0.01078 0.00462 -0.1951 0.7182 1.0000
2.750 1.1356 0.01108 0.00463 -0.1939 0.6638 1.0000
3.000 1.1577 0.01154 0.00477 -0.1924 0.6140 1.0000
3.250 1.1794 0.01204 0.00502 -0.1910 0.5734 1.0000
3.500 1.2011 0.01255 0.00532 -0.1896 0.5366 1.0000
3.750 1.2216 0.01313 0.00569 -0.1881 0.4987 1.0000
4.000 1.2422 0.01372 0.00607 -0.1866 0.4654 1.0000
4.250 1.2636 0.01425 0.00646 -0.1854 0.4401 1.0000
4.500 1.2864 0.01468 0.00686 -0.1844 0.4220 1.0000
4.750 1.3094 0.01508 0.00724 -0.1834 0.4058 1.0000
5.000 1.3322 0.01549 0.00764 -0.1824 0.3873 1.0000
5.250 1.3542 0.01593 0.00806 -0.1813 0.3650 1.0000
5.500 1.3744 0.01647 0.00852 -0.1799 0.3301 1.0000
5.750 1.3906 0.01731 0.00906 -0.1778 0.2706 1.0000
6.000 1.4055 0.01835 0.00977 -0.1756 0.2168 1.0000
6.250 1.4222 0.01926 0.01049 -0.1737 0.1824 1.0000
6.500 1.4400 0.02008 0.01119 -0.1720 0.1547 1.0000
6.750 1.4567 0.02096 0.01196 -0.1702 0.1236 1.0000
7.000 1.4714 0.02200 0.01279 -0.1680 0.0861 1.0000
7.250 1.4854 0.02308 0.01372 -0.1656 0.0626 1.0000
7.500 1.4992 0.02412 0.01471 -0.1632 0.0447 1.0000
7.750 1.5115 0.02527 0.01576 -0.1606 0.0252 1.0000
8.000 1.5230 0.02638 0.01687 -0.1577 0.0204 1.0000
8.250 1.5338 0.02748 0.01808 -0.1546 0.0179 1.0000
8.500 1.5451 0.02854 0.01930 -0.1518 0.0163 1.0000
8.750 1.5550 0.02972 0.02063 -0.1488 0.0149 1.0000
9.000 1.5631 0.03106 0.02212 -0.1456 0.0140 1.0000
9.250 1.5684 0.03262 0.02384 -0.1421 0.0132 1.0000
9.500 1.5702 0.03450 0.02588 -0.1382 0.0126 1.0000
9.750 1.5702 0.03659 0.02812 -0.1343 0.0121 1.0000
10.000 1.5753 0.03829 0.03000 -0.1312 0.0119 1.0000
10.250 1.5803 0.04004 0.03192 -0.1283 0.0114 1.0000
10.500 1.5846 0.04189 0.03393 -0.1255 0.0109 1.0000
10.750 1.5882 0.04388 0.03608 -0.1227 0.0104 1.0000
11.000 1.5908 0.04598 0.03833 -0.1200 0.0098 1.0000
11.250 1.5919 0.04833 0.04085 -0.1174 0.0095 1.0000
11.500 1.5923 0.05083 0.04350 -0.1149 0.0093 1.0000
11.750 1.5917 0.05350 0.04635 -0.1125 0.0091 1.0000
12.000 1.5903 0.05634 0.04935 -0.1102 0.0089 1.0000
12.250 1.5876 0.05942 0.05259 -0.1082 0.0087 1.0000
12.500 1.5837 0.06275 0.05608 -0.1062 0.0085 1.0000
12.750 1.5788 0.06631 0.05982 -0.1045 0.0084 1.0000
13.000 1.5724 0.07023 0.06392 -0.1029 0.0083 1.0000
13.500 1.5558 0.07882 0.07295 -0.1007 0.0081 1.0000
13.750 1.5465 0.08336 0.07774 -0.1004 0.0080 1.0000
14.000 1.5361 0.08832 0.08295 -0.1008 0.0080 1.0000
14.250 1.5245 0.09372 0.08859 -0.1017 0.0080 1.0000
14.500 1.5120 0.09953 0.09464 -0.1032 0.0079 1.0000
14.750 1.4989 0.10577 0.10112 -0.1055 0.0079 1.0000
15.000 1.4853 0.11248 0.10807 -0.1085 0.0079 1.0000
15.250 1.4717 0.11954 0.11535 -0.1120 0.0079 1.0000
15.500 1.4577 0.12712 0.12314 -0.1163 0.0078 1.0000
15.750 1.4436 0.13500 0.13122 -0.1211 0.0079 1.0000
16.000 1.4295 0.14325 0.13966 -0.1264 0.0079 1.0000
16.250 1.4152 0.15205 0.14864 -0.1323 0.0079 1.0000
16.500 1.4014 0.16122 0.15798 -0.1387 0.0079 1.0000
16.750 1.3882 0.17073 0.16762 -0.1453 0.0080 1.0000
17.000 1.3752 0.18095 0.17798 -0.1526 0.0081 1.0000
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