AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH-7-47-6 AIRFOIL (ah7476-il) Reynolds number: 200,000 Max Cl/Cd: 107.24 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah7476-il-200000.txt Download as CSV file: xf-ah7476-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3613 0.10756 0.10426 -0.0145 1.0000 0.0242
-7.250 -0.3695 0.10626 0.10301 -0.0120 1.0000 0.0246
-7.000 -0.3786 0.10503 0.10183 -0.0095 1.0000 0.0250
-6.750 -0.3831 0.10333 0.10017 -0.0083 1.0000 0.0256
-6.500 -0.3846 0.10135 0.09823 -0.0079 1.0000 0.0263
-6.250 -0.3745 0.09858 0.09548 -0.0113 0.9987 0.0272
-6.000 -0.3251 0.09413 0.09097 -0.0304 0.9932 0.0280
-5.750 -0.2936 0.08892 0.08574 -0.0397 0.9891 0.0282
-5.500 -0.2882 0.08481 0.08165 -0.0361 0.9869 0.0287
-5.250 -0.2668 0.08110 0.07793 -0.0387 0.9846 0.0296
-5.000 -0.2419 0.07750 0.07430 -0.0435 0.9804 0.0307
-4.750 -0.2079 0.07347 0.07022 -0.0513 0.9763 0.0329
-4.500 -0.1288 0.06628 0.06286 -0.0746 0.9735 0.0358
-4.250 -0.1080 0.06310 0.05968 -0.0753 0.9715 0.0370
-4.000 -0.0802 0.05997 0.05651 -0.0792 0.9658 0.0389
-3.750 0.0112 0.05277 0.04902 -0.1018 0.9632 0.0452
-3.500 0.0354 0.05050 0.04677 -0.1027 0.9602 0.0480
-3.250 0.1176 0.04472 0.04066 -0.1200 0.9592 0.0566
-3.000 0.1450 0.04278 0.03875 -0.1217 0.9551 0.0600
-2.750 0.2075 0.03871 0.03435 -0.1324 0.9522 0.0697
-2.500 0.2583 0.02119 0.01698 -0.1329 0.9336 0.0841
-2.250 0.3106 0.01820 0.01378 -0.1399 0.9321 0.0978
-2.000 0.3576 0.01580 0.01126 -0.1452 0.9309 0.1133
-1.750 0.3857 0.01465 0.01003 -0.1465 0.9243 0.1288
-1.500 0.4292 0.01300 0.00819 -0.1508 0.9217 0.1549
-1.250 0.4706 0.01140 0.00654 -0.1543 0.9196 0.1843
-0.750 0.5950 0.02171 0.01502 -0.1715 0.9340 0.0797
-0.500 0.6407 0.02051 0.01347 -0.1744 0.9323 0.0675
-0.250 0.6860 0.01907 0.01196 -0.1780 0.9312 0.0644
0.000 0.7164 0.01852 0.01139 -0.1783 0.9249 0.0631
0.250 0.7552 0.01789 0.01077 -0.1803 0.9210 0.0655
0.500 0.7992 0.01707 0.01002 -0.1834 0.9187 0.0653
0.750 0.8448 0.01631 0.00931 -0.1868 0.9170 0.0656
1.000 0.8725 0.01605 0.00908 -0.1864 0.9085 0.0666
1.250 0.9151 0.01536 0.00841 -0.1890 0.9052 0.0710
1.500 0.9603 0.01439 0.00790 -0.1923 0.9026 0.2249
1.750 0.9831 0.01298 0.00783 -0.1908 0.8927 1.0000
2.000 1.0171 0.01245 0.00724 -0.1912 0.8824 1.0000
2.250 1.0512 0.01186 0.00661 -0.1915 0.8684 1.0000
2.500 1.0839 0.01143 0.00613 -0.1916 0.8513 1.0000
2.750 1.1161 0.01118 0.00582 -0.1917 0.8334 1.0000
3.000 1.1457 0.01111 0.00570 -0.1915 0.8133 1.0000
3.250 1.1735 0.01112 0.00566 -0.1909 0.7878 1.0000
3.500 1.1979 0.01122 0.00568 -0.1896 0.7527 1.0000
3.750 1.2215 0.01139 0.00569 -0.1882 0.7047 1.0000
4.000 1.2442 0.01175 0.00576 -0.1866 0.6497 1.0000
4.250 1.2650 0.01233 0.00605 -0.1848 0.5990 1.0000
4.500 1.2852 0.01297 0.00643 -0.1831 0.5551 1.0000
4.750 1.3059 0.01359 0.00685 -0.1815 0.5205 1.0000
5.000 1.3272 0.01415 0.00729 -0.1801 0.4919 1.0000
5.250 1.3481 0.01472 0.00778 -0.1787 0.4640 1.0000
5.500 1.3681 0.01532 0.00827 -0.1771 0.4340 1.0000
5.750 1.3875 0.01593 0.00877 -0.1754 0.4020 1.0000
6.000 1.4069 0.01648 0.00926 -0.1738 0.3668 1.0000
6.250 1.4248 0.01710 0.00975 -0.1719 0.3197 1.0000
6.500 1.4392 0.01804 0.01040 -0.1695 0.2605 1.0000
6.750 1.4526 0.01918 0.01122 -0.1670 0.2117 1.0000
7.000 1.4677 0.02022 0.01208 -0.1648 0.1728 1.0000
7.250 1.4826 0.02130 0.01298 -0.1626 0.1330 1.0000
7.500 1.4917 0.02297 0.01421 -0.1595 0.0766 1.0000
7.750 1.4947 0.02516 0.01616 -0.1551 0.0486 1.0000
8.000 1.5051 0.02651 0.01759 -0.1519 0.0400 1.0000
8.250 1.5121 0.02794 0.01913 -0.1481 0.0362 1.0000
8.500 1.5207 0.02921 0.02051 -0.1446 0.0335 1.0000
8.750 1.5283 0.03061 0.02197 -0.1412 0.0313 1.0000
9.000 1.5295 0.03280 0.02420 -0.1370 0.0294 1.0000
9.250 1.5404 0.03413 0.02567 -0.1342 0.0280 1.0000
9.500 1.5499 0.03575 0.02744 -0.1313 0.0267 1.0000
9.750 1.5600 0.03755 0.02937 -0.1286 0.0257 1.0000
10.000 1.5710 0.03946 0.03140 -0.1260 0.0249 1.0000
10.250 1.5830 0.04152 0.03359 -0.1237 0.0242 1.0000
10.500 1.5961 0.04382 0.03604 -0.1217 0.0236 1.0000
10.750 1.6103 0.04655 0.03893 -0.1199 0.0230 1.0000
11.000 1.6263 0.05109 0.04376 -0.1188 0.0222 1.0000
11.250 1.6252 0.05412 0.04712 -0.1151 0.0218 1.0000
11.500 1.6214 0.05668 0.04999 -0.1113 0.0215 1.0000
11.750 1.6162 0.06008 0.05371 -0.1077 0.0215 1.0000
12.000 1.6073 0.06385 0.05780 -0.1041 0.0215 1.0000
12.250 1.5951 0.06790 0.06216 -0.1008 0.0215 1.0000
12.500 1.5802 0.07232 0.06686 -0.0978 0.0216 1.0000
12.750 1.5630 0.07709 0.07190 -0.0954 0.0217 1.0000
13.000 1.5439 0.08232 0.07740 -0.0936 0.0218 1.0000
13.250 1.5272 0.08818 0.08349 -0.0925 0.0221 1.0000
13.500 1.5103 0.09282 0.08835 -0.0921 0.0222 1.0000
13.750 1.4942 0.09763 0.09338 -0.0926 0.0223 1.0000
14.000 1.4766 0.10306 0.09904 -0.0940 0.0224 1.0000
14.250 1.4573 0.10934 0.10556 -0.0967 0.0227 1.0000
14.500 1.4316 0.11790 0.11441 -0.1016 0.0231 1.0000
14.750 1.2047 0.11120 0.10777 -0.0775 0.0228 1.0000
15.000 1.1719 0.11945 0.11626 -0.0825 0.0232 1.0000
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Polar data table (+)
Polar graphs
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