N-9 (n9-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-9 (n9-il) Reynolds number: 500,000 Max Cl/Cd: 78.27 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n9-il-500000-n5.txt Download as CSV file: xf-n9-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7543 0.03596 0.03309 -0.0586 1.0000 0.0065
-11.000 -0.7563 0.02944 0.02600 -0.0593 1.0000 0.0066
-10.750 -0.7453 0.02620 0.02240 -0.0587 1.0000 0.0068
-10.500 -0.7286 0.02425 0.02021 -0.0580 1.0000 0.0070
-10.250 -0.7099 0.02274 0.01850 -0.0572 1.0000 0.0072
-10.000 -0.6903 0.02142 0.01700 -0.0563 1.0000 0.0075
-9.750 -0.6702 0.02019 0.01558 -0.0553 1.0000 0.0077
-9.500 -0.6497 0.01903 0.01423 -0.0544 1.0000 0.0081
-9.250 -0.6201 0.01786 0.01282 -0.0552 0.9980 0.0085
-9.000 -0.5891 0.01688 0.01164 -0.0562 0.9957 0.0090
-8.750 -0.5589 0.01576 0.01034 -0.0571 0.9929 0.0097
-8.500 -0.5280 0.01500 0.00948 -0.0580 0.9891 0.0104
-8.250 -0.4964 0.01435 0.00872 -0.0590 0.9856 0.0111
-7.750 -0.4364 0.01312 0.00724 -0.0600 0.9737 0.0127
-7.500 -0.4056 0.01249 0.00654 -0.0607 0.9676 0.0142
-7.250 -0.3738 0.01216 0.00620 -0.0615 0.9611 0.0160
-7.000 -0.3408 0.01177 0.00574 -0.0625 0.9545 0.0178
-6.750 -0.3078 0.01130 0.00522 -0.0636 0.9480 0.0198
-6.500 -0.2738 0.01103 0.00492 -0.0649 0.9413 0.0226
-6.250 -0.2402 0.01079 0.00461 -0.0660 0.9339 0.0251
-6.000 -0.2079 0.01044 0.00417 -0.0669 0.9258 0.0272
-5.750 -0.1780 0.01011 0.00382 -0.0673 0.9171 0.0302
-5.500 -0.1487 0.00991 0.00353 -0.0674 0.9089 0.0326
-5.250 -0.1207 0.00974 0.00328 -0.0673 0.8986 0.0345
-5.000 -0.0933 0.00955 0.00301 -0.0670 0.8873 0.0363
-4.750 -0.0661 0.00932 0.00273 -0.0667 0.8754 0.0396
-4.500 -0.0389 0.00914 0.00251 -0.0664 0.8631 0.0424
-4.250 -0.0117 0.00899 0.00230 -0.0661 0.8488 0.0454
-4.000 0.0154 0.00882 0.00212 -0.0658 0.8300 0.0536
-3.750 0.0420 0.00869 0.00197 -0.0653 0.8012 0.0695
-3.500 0.0679 0.00867 0.00182 -0.0647 0.7635 0.0820
-3.250 0.0941 0.00870 0.00169 -0.0642 0.7342 0.0903
-3.000 0.1209 0.00873 0.00160 -0.0638 0.7127 0.0975
-2.750 0.1481 0.00872 0.00151 -0.0636 0.6962 0.1044
-2.500 0.1758 0.00869 0.00144 -0.0635 0.6842 0.1131
-2.000 0.2307 0.00838 0.00136 -0.0634 0.6651 0.2077
-1.750 0.2584 0.00827 0.00133 -0.0634 0.6552 0.2442
-1.500 0.2855 0.00805 0.00131 -0.0633 0.6417 0.3198
-1.250 0.3119 0.00768 0.00133 -0.0633 0.6276 0.4646
-1.000 0.3386 0.00747 0.00135 -0.0631 0.6139 0.5576
-0.750 0.3647 0.00724 0.00137 -0.0628 0.5986 0.6537
-0.500 0.3883 0.00693 0.00141 -0.0617 0.5783 0.7835
-0.250 0.4159 0.00667 0.00146 -0.0610 0.5526 0.9661
0.000 0.4515 0.00681 0.00146 -0.0628 0.5190 1.0000
0.250 0.4771 0.00704 0.00150 -0.0624 0.4788 1.0000
0.500 0.5022 0.00736 0.00159 -0.0619 0.4321 1.0000
0.750 0.5275 0.00769 0.00171 -0.0615 0.3920 1.0000
1.000 0.5534 0.00796 0.00184 -0.0612 0.3633 1.0000
1.250 0.5798 0.00817 0.00196 -0.0610 0.3440 1.0000
1.500 0.6062 0.00839 0.00208 -0.0608 0.3261 1.0000
1.750 0.6328 0.00859 0.00222 -0.0606 0.3118 1.0000
2.000 0.6596 0.00877 0.00235 -0.0605 0.2998 1.0000
2.250 0.6863 0.00896 0.00250 -0.0604 0.2870 1.0000
2.500 0.7128 0.00917 0.00266 -0.0602 0.2701 1.0000
2.750 0.7389 0.00944 0.00283 -0.0600 0.2474 1.0000
3.000 0.7644 0.00978 0.00302 -0.0597 0.2134 1.0000
3.250 0.7863 0.01060 0.00343 -0.0591 0.1317 1.0000
3.500 0.8115 0.01098 0.00374 -0.0588 0.1159 1.0000
3.750 0.8371 0.01131 0.00404 -0.0585 0.1077 1.0000
4.000 0.8633 0.01156 0.00430 -0.0583 0.1036 1.0000
4.250 0.8893 0.01183 0.00460 -0.0581 0.0994 1.0000
4.500 0.9148 0.01215 0.00491 -0.0579 0.0947 1.0000
4.750 0.9402 0.01248 0.00526 -0.0576 0.0910 1.0000
5.000 0.9662 0.01271 0.00554 -0.0574 0.0883 1.0000
5.250 0.9917 0.01299 0.00586 -0.0572 0.0834 1.0000
5.500 1.0166 0.01336 0.00620 -0.0569 0.0774 1.0000
5.750 1.0424 0.01359 0.00648 -0.0568 0.0728 1.0000
6.000 1.0672 0.01394 0.00680 -0.0565 0.0665 1.0000
6.250 1.0922 0.01425 0.00715 -0.0563 0.0617 1.0000
6.500 1.1165 0.01463 0.00751 -0.0559 0.0535 1.0000
6.750 1.1402 0.01508 0.00793 -0.0555 0.0435 1.0000
7.000 1.1625 0.01568 0.00846 -0.0549 0.0304 1.0000
7.250 1.1824 0.01654 0.00923 -0.0540 0.0171 1.0000
7.500 1.2033 0.01728 0.00999 -0.0532 0.0129 1.0000
7.750 1.2253 0.01786 0.01064 -0.0525 0.0116 1.0000
8.000 1.2462 0.01853 0.01141 -0.0517 0.0104 1.0000
8.250 1.2658 0.01934 0.01229 -0.0507 0.0093 1.0000
8.500 1.2853 0.02011 0.01316 -0.0497 0.0087 1.0000
8.750 1.3050 0.02081 0.01396 -0.0488 0.0081 1.0000
9.000 1.3237 0.02157 0.01481 -0.0478 0.0075 1.0000
9.250 1.3414 0.02239 0.01571 -0.0466 0.0070 1.0000
9.500 1.3568 0.02337 0.01677 -0.0452 0.0066 1.0000
9.750 1.3686 0.02462 0.01813 -0.0433 0.0062 1.0000
10.000 1.3824 0.02557 0.01922 -0.0417 0.0060 1.0000
10.250 1.3924 0.02660 0.02037 -0.0395 0.0058 1.0000
10.500 1.4004 0.02773 0.02162 -0.0372 0.0056 1.0000
10.750 1.4071 0.02900 0.02301 -0.0349 0.0055 1.0000
11.000 1.4126 0.03041 0.02455 -0.0328 0.0053 1.0000
11.250 1.4167 0.03201 0.02628 -0.0309 0.0051 1.0000
11.500 1.4199 0.03380 0.02819 -0.0293 0.0050 1.0000
11.750 1.4224 0.03576 0.03027 -0.0279 0.0049 1.0000
12.000 1.4235 0.03798 0.03261 -0.0269 0.0048 1.0000
12.250 1.4233 0.04050 0.03526 -0.0262 0.0046 1.0000
12.500 1.4208 0.04347 0.03837 -0.0260 0.0045 1.0000
12.750 1.4159 0.04699 0.04202 -0.0263 0.0044 1.0000
13.000 1.4072 0.05121 0.04641 -0.0271 0.0044 1.0000
13.250 1.3955 0.05606 0.05141 -0.0284 0.0043 1.0000
13.500 1.3854 0.06092 0.05642 -0.0299 0.0042 1.0000
13.750 1.3747 0.06608 0.06174 -0.0318 0.0042 1.0000
14.000 1.3621 0.07179 0.06762 -0.0341 0.0042 1.0000
14.250 1.3486 0.07794 0.07392 -0.0368 0.0042 1.0000
14.500 1.3331 0.08470 0.08083 -0.0399 0.0041 1.0000
14.750 1.3169 0.09181 0.08809 -0.0432 0.0041 1.0000
15.000 1.2987 0.09935 0.09577 -0.0467 0.0041 1.0000
15.250 1.2803 0.10710 0.10365 -0.0503 0.0041 1.0000
15.500 1.2615 0.11503 0.11171 -0.0541 0.0041 1.0000
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