AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH-7-47-6 AIRFOIL (ah7476-il) Reynolds number: 100,000 Max Cl/Cd: 75.66 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah7476-il-100000.txt Download as CSV file: xf-ah7476-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3512 0.11856 0.11373 -0.0238 1.0000 0.0440
-8.000 -0.3645 0.11862 0.11389 -0.0220 1.0000 0.0441
-7.750 -0.3740 0.11837 0.11374 -0.0217 1.0000 0.0443
-7.500 -0.3767 0.11748 0.11292 -0.0236 1.0000 0.0444
-7.250 -0.3610 0.10840 0.10378 -0.0167 1.0000 0.0463
-7.000 -0.3624 0.10619 0.10162 -0.0150 1.0000 0.0474
-6.750 -0.3639 0.10416 0.09964 -0.0139 1.0000 0.0487
-6.500 -0.3646 0.10214 0.09767 -0.0134 1.0000 0.0501
-6.250 -0.3639 0.10008 0.09565 -0.0136 1.0000 0.0518
-6.000 -0.3594 0.09835 0.09397 -0.0165 1.0000 0.0538
-5.750 -0.3302 0.09756 0.09318 -0.0333 1.0000 0.0553
-5.500 -0.3436 0.09245 0.08814 -0.0220 1.0000 0.0565
-5.250 -0.3407 0.08949 0.08521 -0.0192 1.0000 0.0587
-5.000 -0.3304 0.08677 0.08249 -0.0206 1.0000 0.0617
-4.750 -0.2582 0.08431 0.07981 -0.0479 1.0000 0.0674
-4.500 -0.2681 0.07968 0.07532 -0.0403 1.0000 0.0683
-4.250 -0.2676 0.07659 0.07226 -0.0360 1.0000 0.0700
-4.000 -0.2522 0.07372 0.06938 -0.0371 1.0000 0.0737
-3.750 -0.1896 0.06916 0.06465 -0.0549 1.0000 0.0817
-3.500 -0.1881 0.06652 0.06208 -0.0505 1.0000 0.0849
-3.250 -0.1290 0.06246 0.05782 -0.0648 1.0000 0.0959
-3.000 -0.0824 0.06010 0.05526 -0.0735 1.0000 0.1083
-2.750 -0.0696 0.05640 0.05166 -0.0726 1.0000 0.1115
-2.500 -0.0242 0.05350 0.04860 -0.0806 1.0000 0.1250
-2.250 0.0115 0.05103 0.04604 -0.0855 1.0000 0.1397
-2.000 0.0445 0.04874 0.04367 -0.0894 1.0000 0.1548
-1.750 0.0787 0.04658 0.04145 -0.0933 1.0000 0.1699
-0.500 0.4079 0.03368 0.02639 -0.1384 0.9804 0.1391
-0.250 0.4666 0.03153 0.02359 -0.1438 0.9767 0.1061
0.000 0.5220 0.03031 0.02186 -0.1488 0.9731 0.0959
0.250 0.5663 0.02956 0.02099 -0.1522 0.9665 0.0975
0.500 0.6142 0.02896 0.02023 -0.1560 0.9606 0.0957
0.750 0.6582 0.02843 0.01970 -0.1591 0.9534 0.0955
1.000 0.7060 0.02786 0.01921 -0.1630 0.9468 0.0977
1.250 0.7465 0.02756 0.01892 -0.1655 0.9375 0.1028
1.500 0.7971 0.02705 0.01845 -0.1696 0.9313 0.1194
1.750 0.8320 0.02528 0.01840 -0.1709 0.9211 1.0000
2.000 0.8706 0.02508 0.01804 -0.1725 0.9100 1.0000
2.250 0.9197 0.02451 0.01737 -0.1759 0.9027 1.0000
2.500 0.9564 0.02406 0.01691 -0.1770 0.8899 1.0000
2.750 0.9942 0.02348 0.01634 -0.1781 0.8771 1.0000
3.000 1.0356 0.02249 0.01541 -0.1794 0.8640 1.0000
3.250 1.0827 0.02092 0.01389 -0.1810 0.8499 1.0000
3.500 1.1274 0.01949 0.01254 -0.1823 0.8338 1.0000
3.750 1.1700 0.01844 0.01156 -0.1836 0.8166 1.0000
4.000 1.2022 0.01793 0.01110 -0.1831 0.7907 1.0000
4.250 1.2348 0.01751 0.01071 -0.1828 0.7609 1.0000
4.500 1.2652 0.01728 0.01049 -0.1822 0.7261 1.0000
4.750 1.2926 0.01725 0.01038 -0.1811 0.6861 1.0000
5.000 1.3188 0.01743 0.01040 -0.1799 0.6447 1.0000
5.250 1.3427 0.01788 0.01064 -0.1784 0.6040 1.0000
5.500 1.3649 0.01848 0.01109 -0.1767 0.5662 1.0000
5.750 1.3850 0.01915 0.01166 -0.1748 0.5295 1.0000
6.000 1.4042 0.01988 0.01226 -0.1728 0.4939 1.0000
6.250 1.4222 0.02067 0.01294 -0.1706 0.4583 1.0000
6.500 1.4378 0.02149 0.01371 -0.1680 0.4190 1.0000
6.750 1.4507 0.02231 0.01445 -0.1650 0.3741 1.0000
7.000 1.4612 0.02313 0.01515 -0.1617 0.3210 1.0000
7.250 1.4694 0.02427 0.01597 -0.1581 0.2635 1.0000
7.500 1.4762 0.02583 0.01718 -0.1546 0.2124 1.0000
7.750 1.4818 0.02766 0.01872 -0.1509 0.1627 1.0000
8.000 1.4827 0.02991 0.02058 -0.1464 0.1126 1.0000
8.250 1.4809 0.03240 0.02280 -0.1413 0.0822 1.0000
8.500 1.4813 0.03471 0.02504 -0.1366 0.0708 1.0000
8.750 1.4883 0.03685 0.02716 -0.1331 0.0632 1.0000
9.000 1.5019 0.03924 0.02963 -0.1308 0.0571 1.0000
9.250 1.5186 0.04140 0.03184 -0.1290 0.0522 1.0000
9.500 1.5615 0.04584 0.03628 -0.1316 0.0484 1.0000
9.750 1.5836 0.04872 0.03958 -0.1303 0.0468 1.0000
10.000 1.5979 0.05155 0.04280 -0.1281 0.0449 1.0000
10.250 1.6076 0.05430 0.04587 -0.1254 0.0430 1.0000
10.500 1.6160 0.05737 0.04923 -0.1228 0.0417 1.0000
10.750 1.6180 0.06097 0.05323 -0.1192 0.0414 1.0000
11.000 1.6109 0.06451 0.05718 -0.1146 0.0414 1.0000
11.250 1.5972 0.06814 0.06123 -0.1094 0.0417 1.0000
11.500 1.5791 0.07203 0.06552 -0.1045 0.0420 1.0000
11.750 1.5578 0.07624 0.07011 -0.1001 0.0424 1.0000
12.000 1.5347 0.08085 0.07507 -0.0965 0.0429 1.0000
12.250 1.5101 0.08586 0.08041 -0.0939 0.0433 1.0000
12.500 1.4844 0.09132 0.08616 -0.0925 0.0438 1.0000
12.750 1.4578 0.09734 0.09245 -0.0924 0.0442 1.0000
13.000 1.4306 0.10403 0.09938 -0.0938 0.0447 1.0000
13.250 1.4033 0.11151 0.10708 -0.0967 0.0451 1.0000
13.500 1.3758 0.12003 0.11580 -0.1014 0.0457 1.0000
13.750 1.3487 0.12981 0.12573 -0.1079 0.0463 1.0000
14.000 1.3236 0.14077 0.13681 -0.1157 0.0471 1.0000
14.250 1.3045 0.15145 0.14753 -0.1227 0.0480 1.0000
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