AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH-7-47-6 AIRFOIL (ah7476-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.11 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah7476-il-1000000.txt Download as CSV file: xf-ah7476-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2750 0.10701 0.10533 -0.0446 0.9932 0.0111
-8.750 -0.2640 0.10355 0.10187 -0.0478 0.9911 0.0111
-8.500 -0.2514 0.09998 0.09830 -0.0513 0.9892 0.0111
-8.250 -0.2393 0.09579 0.09411 -0.0529 0.9881 0.0113
-8.000 -0.2236 0.09268 0.09100 -0.0558 0.9869 0.0115
-7.750 -0.2060 0.08957 0.08789 -0.0594 0.9856 0.0118
-7.500 -0.1864 0.08629 0.08461 -0.0638 0.9844 0.0122
-7.250 -0.1716 0.08318 0.08150 -0.0667 0.9803 0.0131
-7.000 -0.0507 0.05734 0.05572 -0.0879 0.9728 0.0143
-6.500 -0.0783 0.06883 0.06710 -0.0949 0.9735 0.0143
-6.250 -0.0558 0.06449 0.06275 -0.0988 0.9728 0.0146
-6.000 -0.0258 0.06143 0.05968 -0.1042 0.9722 0.0149
-5.750 0.0085 0.05808 0.05631 -0.1112 0.9714 0.0157
-5.500 0.0436 0.05405 0.05225 -0.1197 0.9651 0.0177
-5.250 0.0982 0.04807 0.04618 -0.1339 0.9631 0.0179
-5.000 0.1530 0.04026 0.03825 -0.1485 0.9616 0.0182
-4.750 0.1840 0.03791 0.03587 -0.1524 0.9600 0.0185
-4.500 0.2207 0.03538 0.03329 -0.1575 0.9586 0.0190
-4.250 0.2569 0.03253 0.03037 -0.1624 0.9546 0.0198
-4.000 0.3195 0.02687 0.02440 -0.1727 0.9517 0.0223
-3.750 0.3690 0.02241 0.01955 -0.1796 0.9488 0.0224
-3.500 0.4133 0.01756 0.01440 -0.1861 0.9461 0.0231
-3.250 0.4450 0.01628 0.01303 -0.1878 0.9408 0.0236
-3.000 0.4763 0.01519 0.01184 -0.1891 0.9350 0.0242
-2.750 0.5104 0.01400 0.01048 -0.1909 0.9303 0.0256
-2.500 0.5404 0.01399 0.01023 -0.1907 0.9217 0.0279
-2.250 0.5730 0.01329 0.00928 -0.1917 0.9147 0.0281
-2.000 0.6089 0.01071 0.00647 -0.1943 0.9072 0.0294
-1.750 0.6391 0.01006 0.00576 -0.1950 0.8988 0.0303
-1.500 0.6689 0.00958 0.00518 -0.1955 0.8899 0.0313
-1.250 0.6983 0.00926 0.00478 -0.1957 0.8805 0.0331
-1.000 0.7260 0.00952 0.00495 -0.1955 0.8708 0.0351
-0.750 0.7576 0.00834 0.00365 -0.1965 0.8612 0.0384
-0.500 0.7864 0.00808 0.00336 -0.1967 0.8515 0.0410
-0.250 0.8146 0.00805 0.00327 -0.1967 0.8421 0.0439
0.000 0.8444 0.00749 0.00264 -0.1971 0.8300 0.0468
0.250 0.8729 0.00738 0.00240 -0.1968 0.8155 0.0367
0.500 0.9003 0.00741 0.00238 -0.1965 0.8008 0.0357
0.750 0.9286 0.00727 0.00220 -0.1966 0.7845 0.0342
1.000 0.9560 0.00725 0.00212 -0.1964 0.7636 0.0344
1.250 0.9829 0.00729 0.00206 -0.1961 0.7372 0.0343
1.500 1.0070 0.00753 0.00205 -0.1952 0.6805 0.0336
1.750 1.0285 0.00808 0.00219 -0.1938 0.6007 0.0333
2.000 1.0520 0.00852 0.00235 -0.1929 0.5419 0.0333
2.250 1.0759 0.00894 0.00251 -0.1921 0.4897 0.0338
2.500 1.1012 0.00922 0.00264 -0.1917 0.4604 0.0350
2.750 1.1273 0.00942 0.00275 -0.1913 0.4418 0.0373
3.000 1.1535 0.00960 0.00289 -0.1910 0.4273 0.0409
3.250 1.1806 0.00967 0.00311 -0.1909 0.4143 0.1579
3.500 1.2057 0.00873 0.00356 -0.1910 0.3994 1.0000
3.750 1.2314 0.00897 0.00373 -0.1905 0.3793 1.0000
4.000 1.2564 0.00928 0.00391 -0.1900 0.3541 1.0000
4.250 1.2808 0.00963 0.00413 -0.1894 0.3203 1.0000
4.500 1.3024 0.01030 0.00447 -0.1883 0.2604 1.0000
5.000 1.3464 0.01152 0.00524 -0.1862 0.1798 1.0000
5.250 1.3692 0.01204 0.00561 -0.1853 0.1517 1.0000
5.500 1.3914 0.01259 0.00600 -0.1843 0.1207 1.0000
5.750 1.4120 0.01333 0.00649 -0.1831 0.0805 1.0000
6.000 1.4334 0.01395 0.00697 -0.1819 0.0582 1.0000
6.250 1.4560 0.01443 0.00741 -0.1809 0.0463 1.0000
6.500 1.4747 0.01532 0.00807 -0.1793 0.0197 1.0000
6.750 1.4964 0.01586 0.00862 -0.1781 0.0157 1.0000
7.000 1.5183 0.01635 0.00915 -0.1769 0.0143 1.0000
7.250 1.5388 0.01696 0.00980 -0.1755 0.0129 1.0000
7.500 1.5577 0.01774 0.01069 -0.1738 0.0117 1.0000
7.750 1.5785 0.01825 0.01125 -0.1724 0.0113 1.0000
8.000 1.5982 0.01882 0.01188 -0.1709 0.0108 1.0000
8.250 1.6171 0.01943 0.01254 -0.1693 0.0102 1.0000
8.500 1.6351 0.02007 0.01323 -0.1675 0.0096 1.0000
8.750 1.6505 0.02088 0.01410 -0.1652 0.0091 1.0000
9.000 1.6589 0.02221 0.01556 -0.1616 0.0085 1.0000
9.250 1.6681 0.02336 0.01682 -0.1582 0.0082 1.0000
9.500 1.6815 0.02405 0.01757 -0.1556 0.0080 1.0000
9.750 1.6921 0.02487 0.01848 -0.1525 0.0078 1.0000
10.000 1.7013 0.02584 0.01954 -0.1492 0.0076 1.0000
10.250 1.7102 0.02685 0.02064 -0.1460 0.0074 1.0000
10.500 1.7180 0.02798 0.02186 -0.1427 0.0072 1.0000
10.750 1.7251 0.02919 0.02317 -0.1395 0.0070 1.0000
11.000 1.7320 0.03043 0.02450 -0.1363 0.0068 1.0000
11.250 1.7387 0.03172 0.02588 -0.1333 0.0066 1.0000
11.500 1.7446 0.03309 0.02733 -0.1303 0.0064 1.0000
11.750 1.7490 0.03462 0.02894 -0.1272 0.0063 1.0000
12.000 1.7500 0.03650 0.03091 -0.1239 0.0061 1.0000
12.250 1.7413 0.03940 0.03396 -0.1196 0.0059 1.0000
12.500 1.7257 0.04332 0.03809 -0.1149 0.0057 1.0000
12.750 1.7312 0.04492 0.03981 -0.1129 0.0056 1.0000
13.000 1.7337 0.04695 0.04196 -0.1107 0.0055 1.0000
13.250 1.7322 0.04952 0.04466 -0.1084 0.0055 1.0000
13.500 1.7308 0.05214 0.04742 -0.1064 0.0054 1.0000
13.750 1.7262 0.05524 0.05067 -0.1045 0.0053 1.0000
14.000 1.7207 0.05857 0.05415 -0.1029 0.0052 1.0000
14.250 1.7127 0.06239 0.05813 -0.1015 0.0052 1.0000
14.500 1.7056 0.06625 0.06214 -0.1006 0.0051 1.0000
14.750 1.6953 0.07077 0.06682 -0.1001 0.0050 1.0000
15.000 1.6847 0.07561 0.07182 -0.1001 0.0050 1.0000
15.250 1.6719 0.08105 0.07743 -0.1006 0.0049 1.0000
15.500 1.6593 0.08673 0.08327 -0.1018 0.0049 1.0000
15.750 1.6453 0.09291 0.08962 -0.1034 0.0049 1.0000
16.000 1.6305 0.09955 0.09642 -0.1057 0.0049 1.0000
16.250 1.6149 0.10661 0.10365 -0.1086 0.0048 1.0000
16.500 1.5978 0.11419 0.11140 -0.1119 0.0048 1.0000
16.750 1.5808 0.12195 0.11931 -0.1157 0.0048 1.0000
17.000 1.5646 0.12981 0.12732 -0.1199 0.0048 1.0000
17.250 1.5456 0.13855 0.13623 -0.1248 0.0048 1.0000
17.500 1.5278 0.14740 0.14523 -0.1302 0.0049 1.0000
17.750 1.5109 0.15646 0.15444 -0.1359 0.0049 1.0000
18.000 1.4916 0.16662 0.16476 -0.1426 0.0049 1.0000
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