AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH-7-47-6 AIRFOIL (ah7476-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.2 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah7476-il-1000000-n5.txt Download as CSV file: xf-ah7476-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1915 0.09588 0.09410 -0.0698 0.9856 0.0053
-8.750 -0.1814 0.09276 0.09098 -0.0718 0.9833 0.0054
-8.500 -0.1688 0.08938 0.08761 -0.0747 0.9817 0.0057
-8.250 -0.1552 0.08564 0.08386 -0.0782 0.9803 0.0060
-8.000 -0.1422 0.08116 0.07938 -0.0825 0.9785 0.0064
-7.750 -0.1340 0.07692 0.07515 -0.0858 0.9733 0.0068
-7.500 -0.1140 0.07437 0.07260 -0.0895 0.9707 0.0070
-7.250 -0.0919 0.07169 0.06991 -0.0937 0.9687 0.0074
-7.000 -0.0761 0.06894 0.06716 -0.0967 0.9630 0.0078
-6.750 -0.0526 0.06468 0.06288 -0.1031 0.9595 0.0084
-6.500 -0.0279 0.05860 0.05676 -0.1122 0.9531 0.0093
-6.250 -0.0007 0.05603 0.05418 -0.1171 0.9494 0.0095
-6.000 0.0263 0.05352 0.05164 -0.1217 0.9446 0.0099
-5.750 0.0577 0.05016 0.04825 -0.1281 0.9392 0.0107
-5.250 0.1428 0.04005 0.03797 -0.1488 0.9279 0.0125
-5.000 0.1794 0.03748 0.03534 -0.1544 0.9229 0.0132
-4.750 0.2583 0.02668 0.02419 -0.1751 0.9188 0.0156
-4.500 0.2907 0.02537 0.02279 -0.1776 0.9117 0.0159
-4.250 0.3246 0.02374 0.02104 -0.1805 0.9027 0.0164
-4.000 0.3687 0.02008 0.01710 -0.1861 0.8933 0.0172
-3.750 0.4232 0.01450 0.01066 -0.1934 0.8825 0.0193
-3.500 0.4560 0.01306 0.00899 -0.1953 0.8677 0.0197
-3.250 0.4862 0.01242 0.00820 -0.1962 0.8554 0.0199
-3.000 0.5164 0.01184 0.00747 -0.1970 0.8454 0.0202
-2.750 0.5466 0.01126 0.00671 -0.1977 0.8353 0.0204
-2.500 0.5769 0.01070 0.00599 -0.1984 0.8251 0.0206
-2.250 0.6068 0.01022 0.00535 -0.1989 0.8161 0.0208
-2.000 0.6363 0.00985 0.00488 -0.1993 0.8082 0.0211
-1.750 0.6663 0.00939 0.00429 -0.1999 0.8021 0.0211
-1.500 0.6960 0.00900 0.00381 -0.2003 0.7953 0.0212
-1.250 0.7251 0.00870 0.00343 -0.2006 0.7885 0.0214
-1.000 0.7542 0.00845 0.00313 -0.2009 0.7804 0.0218
-0.750 0.7829 0.00828 0.00290 -0.2010 0.7712 0.0223
-0.500 0.8110 0.00818 0.00274 -0.2011 0.7599 0.0229
-0.250 0.8392 0.00810 0.00262 -0.2012 0.7470 0.0232
0.000 0.8663 0.00810 0.00253 -0.2010 0.7226 0.0235
0.250 0.8901 0.00838 0.00252 -0.2001 0.6623 0.0236
0.500 0.9128 0.00883 0.00262 -0.1991 0.5924 0.0238
0.750 0.9377 0.00907 0.00260 -0.1986 0.5333 0.0243
1.000 0.9628 0.00933 0.00263 -0.1982 0.4814 0.0248
1.250 0.9886 0.00955 0.00270 -0.1979 0.4488 0.0248
1.750 1.0414 0.00986 0.00282 -0.1974 0.4055 0.0249
2.000 1.0685 0.00994 0.00287 -0.1973 0.3941 0.0252
2.250 1.0954 0.01004 0.00294 -0.1972 0.3815 0.0257
2.500 1.1221 0.01016 0.00302 -0.1970 0.3683 0.0265
2.750 1.1486 0.01029 0.00312 -0.1967 0.3567 0.0277
3.000 1.1747 0.01047 0.00324 -0.1964 0.3396 0.0287
3.250 1.1996 0.01076 0.00341 -0.1959 0.3105 0.0294
3.500 1.2227 0.01123 0.00367 -0.1951 0.2649 0.0305
3.750 1.2456 0.01173 0.00397 -0.1942 0.2255 0.0327
4.000 1.2677 0.01231 0.00433 -0.1932 0.1827 0.0341
4.250 1.2913 0.01272 0.00464 -0.1925 0.1554 0.0663
4.750 1.3387 0.01249 0.00562 -0.1916 0.1069 1.0000
5.250 1.3829 0.01361 0.00644 -0.1896 0.0544 1.0000
5.500 1.4066 0.01396 0.00677 -0.1888 0.0478 1.0000
5.750 1.4300 0.01432 0.00711 -0.1880 0.0409 1.0000
6.000 1.4500 0.01506 0.00767 -0.1866 0.0172 1.0000
6.250 1.4724 0.01550 0.00811 -0.1856 0.0125 1.0000
6.500 1.4953 0.01586 0.00850 -0.1847 0.0112 1.0000
6.750 1.5175 0.01628 0.00894 -0.1837 0.0099 1.0000
7.000 1.5387 0.01677 0.00946 -0.1824 0.0085 1.0000
7.250 1.5602 0.01720 0.00993 -0.1813 0.0078 1.0000
7.500 1.5815 0.01763 0.01040 -0.1801 0.0072 1.0000
7.750 1.6019 0.01810 0.01090 -0.1788 0.0065 1.0000
8.000 1.6213 0.01864 0.01146 -0.1772 0.0060 1.0000
8.250 1.6388 0.01931 0.01219 -0.1753 0.0054 1.0000
8.500 1.6574 0.01982 0.01275 -0.1736 0.0052 1.0000
8.750 1.6752 0.02037 0.01337 -0.1718 0.0050 1.0000
9.000 1.6919 0.02097 0.01402 -0.1698 0.0048 1.0000
9.250 1.7076 0.02159 0.01470 -0.1677 0.0045 1.0000
9.500 1.7217 0.02223 0.01541 -0.1652 0.0043 1.0000
9.750 1.7347 0.02290 0.01613 -0.1625 0.0041 1.0000
10.000 1.7469 0.02365 0.01693 -0.1598 0.0038 1.0000
10.250 1.7564 0.02463 0.01799 -0.1567 0.0036 1.0000
10.500 1.7660 0.02561 0.01906 -0.1536 0.0034 1.0000
10.750 1.7769 0.02650 0.02004 -0.1509 0.0034 1.0000
11.000 1.7871 0.02745 0.02107 -0.1481 0.0033 1.0000
11.250 1.7961 0.02851 0.02222 -0.1452 0.0032 1.0000
11.500 1.8044 0.02964 0.02345 -0.1424 0.0031 1.0000
11.750 1.8118 0.03085 0.02476 -0.1395 0.0030 1.0000
12.000 1.8184 0.03216 0.02616 -0.1366 0.0029 1.0000
12.250 1.8244 0.03354 0.02765 -0.1337 0.0028 1.0000
12.500 1.8295 0.03502 0.02922 -0.1309 0.0027 1.0000
12.750 1.8338 0.03661 0.03092 -0.1281 0.0027 1.0000
13.000 1.8376 0.03831 0.03273 -0.1255 0.0026 1.0000
13.250 1.8401 0.04017 0.03469 -0.1229 0.0025 1.0000
13.500 1.8421 0.04213 0.03676 -0.1204 0.0025 1.0000
13.750 1.8424 0.04433 0.03907 -0.1180 0.0024 1.0000
14.000 1.8419 0.04672 0.04157 -0.1158 0.0024 1.0000
14.250 1.8390 0.04944 0.04441 -0.1136 0.0023 1.0000
14.500 1.8357 0.05229 0.04738 -0.1118 0.0023 1.0000
14.750 1.8292 0.05570 0.05092 -0.1100 0.0022 1.0000
15.000 1.8212 0.05947 0.05483 -0.1086 0.0022 1.0000
15.250 1.8113 0.06371 0.05924 -0.1076 0.0022 1.0000
15.500 1.7973 0.06875 0.06443 -0.1071 0.0021 1.0000
15.750 1.7831 0.07415 0.07000 -0.1072 0.0021 1.0000
16.000 1.7677 0.08008 0.07610 -0.1079 0.0021 1.0000
16.250 1.7523 0.08632 0.08249 -0.1092 0.0021 1.0000
16.500 1.7393 0.09235 0.08867 -0.1107 0.0020 1.0000
16.750 1.7209 0.09959 0.09608 -0.1130 0.0020 1.0000
17.000 1.7075 0.10612 0.10275 -0.1154 0.0020 1.0000
17.250 1.6905 0.11344 0.11022 -0.1183 0.0020 1.0000
17.500 1.6708 0.12135 0.11828 -0.1217 0.0020 1.0000
17.750 1.6537 0.12892 0.12599 -0.1251 0.0020 1.0000
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