N-9 (n9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-9 (n9-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.64 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n9-il-1000000.txt Download as CSV file: xf-n9-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: N-9
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5141 0.12589 0.12417 -0.0003 1.0000 0.0120
-12.250 -0.5105 0.12197 0.12026 -0.0019 1.0000 0.0126
-11.250 -0.7952 0.02868 0.02600 -0.0577 1.0000 0.0089
-11.000 -0.7848 0.02551 0.02248 -0.0569 1.0000 0.0091
-10.750 -0.7698 0.02324 0.01994 -0.0559 1.0000 0.0094
-10.500 -0.7526 0.02138 0.01782 -0.0549 1.0000 0.0096
-10.250 -0.7336 0.01987 0.01610 -0.0539 1.0000 0.0099
-10.000 -0.7131 0.01871 0.01475 -0.0528 1.0000 0.0101
-9.750 -0.6914 0.01791 0.01381 -0.0518 1.0000 0.0103
-9.500 -0.6748 0.01552 0.01106 -0.0505 1.0000 0.0109
-9.250 -0.6531 0.01488 0.01036 -0.0494 1.0000 0.0114
-9.000 -0.6270 0.01451 0.00995 -0.0492 0.9995 0.0119
-8.750 -0.5937 0.01406 0.00943 -0.0504 0.9982 0.0125
-8.500 -0.5604 0.01354 0.00883 -0.0516 0.9967 0.0132
-8.250 -0.5271 0.01307 0.00825 -0.0528 0.9952 0.0136
-8.000 -0.4957 0.01184 0.00688 -0.0538 0.9936 0.0147
-7.750 -0.4635 0.01150 0.00652 -0.0547 0.9908 0.0156
-7.500 -0.4306 0.01117 0.00616 -0.0558 0.9880 0.0166
-7.250 -0.3970 0.01086 0.00580 -0.0569 0.9856 0.0176
-7.000 -0.3651 0.01019 0.00507 -0.0579 0.9825 0.0191
-6.750 -0.3343 0.00997 0.00486 -0.0584 0.9768 0.0205
-6.250 -0.2688 0.00953 0.00437 -0.0603 0.9651 0.0232
-6.000 -0.2348 0.00885 0.00363 -0.0616 0.9566 0.0258
-5.750 -0.2001 0.00862 0.00338 -0.0630 0.9449 0.0280
-5.250 -0.1404 0.00818 0.00278 -0.0634 0.9195 0.0312
-5.000 -0.1132 0.00790 0.00244 -0.0631 0.9082 0.0345
-4.750 -0.0858 0.00776 0.00226 -0.0628 0.8982 0.0368
-4.500 -0.0585 0.00767 0.00208 -0.0625 0.8881 0.0387
-4.250 -0.0311 0.00746 0.00185 -0.0622 0.8770 0.0427
-4.000 -0.0038 0.00731 0.00168 -0.0619 0.8642 0.0482
-3.750 0.0233 0.00711 0.00155 -0.0616 0.8483 0.0689
-3.500 0.0505 0.00703 0.00146 -0.0612 0.8257 0.0865
-3.250 0.0770 0.00700 0.00133 -0.0608 0.7878 0.0960
-3.000 0.1034 0.00707 0.00123 -0.0603 0.7516 0.1019
-2.750 0.1304 0.00705 0.00115 -0.0600 0.7294 0.1122
-2.500 0.1579 0.00702 0.00108 -0.0599 0.7140 0.1258
-2.250 0.1852 0.00682 0.00106 -0.0598 0.7002 0.2019
-2.000 0.2127 0.00671 0.00104 -0.0597 0.6858 0.2450
-1.750 0.2401 0.00651 0.00101 -0.0597 0.6732 0.3184
-1.500 0.2669 0.00610 0.00102 -0.0597 0.6628 0.4701
-1.250 0.2929 0.00565 0.00104 -0.0595 0.6495 0.6416
-1.000 0.3167 0.00519 0.00108 -0.0586 0.6364 0.8133
-0.750 0.3381 0.00492 0.00114 -0.0566 0.6251 0.9527
-0.500 0.3772 0.00496 0.00113 -0.0589 0.6106 0.9906
-0.250 0.4125 0.00503 0.00114 -0.0606 0.5956 1.0000
0.000 0.4390 0.00513 0.00115 -0.0603 0.5774 1.0000
0.250 0.4655 0.00525 0.00117 -0.0599 0.5515 1.0000
0.500 0.4916 0.00543 0.00120 -0.0596 0.5161 1.0000
0.750 0.5166 0.00576 0.00128 -0.0591 0.4562 1.0000
1.000 0.5419 0.00611 0.00139 -0.0586 0.4061 1.0000
1.250 0.5679 0.00638 0.00151 -0.0584 0.3735 1.0000
1.500 0.5946 0.00658 0.00162 -0.0582 0.3512 1.0000
1.750 0.6213 0.00679 0.00173 -0.0580 0.3315 1.0000
2.000 0.6481 0.00698 0.00185 -0.0579 0.3151 1.0000
2.250 0.6750 0.00716 0.00197 -0.0577 0.2996 1.0000
2.500 0.7019 0.00734 0.00209 -0.0576 0.2837 1.0000
2.750 0.7287 0.00754 0.00222 -0.0575 0.2633 1.0000
3.000 0.7543 0.00789 0.00239 -0.0573 0.2240 1.0000
3.250 0.7759 0.00880 0.00282 -0.0565 0.1276 1.0000
3.500 0.8018 0.00913 0.00308 -0.0562 0.1137 1.0000
3.750 0.8280 0.00940 0.00332 -0.0561 0.1066 1.0000
4.000 0.8543 0.00967 0.00358 -0.0559 0.1009 1.0000
4.250 0.8812 0.00985 0.00378 -0.0558 0.0978 1.0000
4.500 0.9074 0.01010 0.00401 -0.0557 0.0924 1.0000
4.750 0.9334 0.01039 0.00431 -0.0555 0.0871 1.0000
5.000 0.9603 0.01054 0.00448 -0.0555 0.0844 1.0000
5.250 0.9866 0.01076 0.00470 -0.0553 0.0804 1.0000
5.500 1.0121 0.01109 0.00500 -0.0551 0.0745 1.0000
5.750 1.0388 0.01124 0.00519 -0.0551 0.0720 1.0000
6.000 1.0649 0.01147 0.00541 -0.0550 0.0673 1.0000
6.250 1.0904 0.01176 0.00568 -0.0548 0.0617 1.0000
6.500 1.1161 0.01201 0.00593 -0.0547 0.0559 1.0000
6.750 1.1409 0.01238 0.00625 -0.0544 0.0463 1.0000
7.000 1.1635 0.01300 0.00674 -0.0538 0.0298 1.0000
7.250 1.1851 0.01375 0.00740 -0.0531 0.0189 1.0000
7.500 1.2078 0.01434 0.00801 -0.0524 0.0160 1.0000
7.750 1.2303 0.01494 0.00867 -0.0518 0.0142 1.0000
8.000 1.2533 0.01546 0.00924 -0.0512 0.0132 1.0000
8.250 1.2753 0.01605 0.00988 -0.0506 0.0122 1.0000
8.500 1.2941 0.01702 0.01093 -0.0494 0.0109 1.0000
8.750 1.3159 0.01759 0.01156 -0.0487 0.0105 1.0000
9.000 1.3371 0.01819 0.01223 -0.0480 0.0101 1.0000
9.250 1.3573 0.01886 0.01298 -0.0471 0.0096 1.0000
9.500 1.3768 0.01957 0.01375 -0.0462 0.0091 1.0000
9.750 1.3950 0.02036 0.01462 -0.0451 0.0087 1.0000
10.000 1.4096 0.02146 0.01580 -0.0435 0.0083 1.0000
10.250 1.4144 0.02334 0.01784 -0.0406 0.0079 1.0000
10.500 1.4305 0.02410 0.01869 -0.0393 0.0077 1.0000
10.750 1.4436 0.02496 0.01965 -0.0375 0.0076 1.0000
11.000 1.4537 0.02586 0.02063 -0.0353 0.0074 1.0000
11.250 1.4624 0.02688 0.02175 -0.0331 0.0072 1.0000
11.500 1.4704 0.02799 0.02295 -0.0310 0.0069 1.0000
11.750 1.4767 0.02929 0.02435 -0.0291 0.0068 1.0000
12.000 1.4823 0.03074 0.02589 -0.0274 0.0066 1.0000
12.250 1.4859 0.03246 0.02771 -0.0259 0.0064 1.0000
12.500 1.4888 0.03435 0.02970 -0.0246 0.0063 1.0000
12.750 1.4898 0.03656 0.03202 -0.0237 0.0062 1.0000
13.000 1.4881 0.03923 0.03480 -0.0231 0.0061 1.0000
13.250 1.4833 0.04252 0.03822 -0.0230 0.0059 1.0000
13.500 1.4751 0.04648 0.04233 -0.0235 0.0059 1.0000
13.750 1.4626 0.05125 0.04725 -0.0245 0.0058 1.0000
14.000 1.4467 0.05671 0.05287 -0.0260 0.0057 1.0000
14.250 1.4315 0.06234 0.05865 -0.0279 0.0057 1.0000
14.500 1.4097 0.06919 0.06567 -0.0304 0.0056 1.0000
14.750 1.3918 0.07588 0.07252 -0.0333 0.0056 1.0000
15.000 1.3731 0.08298 0.07976 -0.0365 0.0056 1.0000
15.250 1.3530 0.09061 0.08753 -0.0400 0.0056 1.0000
15.500 1.3327 0.09843 0.09549 -0.0436 0.0056 1.0000
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Polar data table (+)
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