SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7084 (9.6%) (sd7084-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.89 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7084-il-1000000.txt Download as CSV file: xf-sd7084-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD7084 (9.6%)
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 -0.4683 0.04602 0.04465 -0.0471 1.0000 0.0102
-8.500 -0.6000 0.02849 0.02575 -0.0611 0.9885 0.0090
-8.250 -0.5739 0.02581 0.02272 -0.0628 0.9863 0.0095
-8.000 -0.5549 0.02087 0.01719 -0.0644 0.9835 0.0104
-7.750 -0.5294 0.01984 0.01604 -0.0647 0.9795 0.0107
-7.500 -0.5022 0.01917 0.01529 -0.0651 0.9757 0.0111
-7.250 -0.4768 0.01793 0.01387 -0.0651 0.9718 0.0115
-7.000 -0.4549 0.01675 0.01250 -0.0642 0.9664 0.0119
-6.750 -0.4327 0.01576 0.01135 -0.0632 0.9610 0.0123
-6.500 -0.4100 0.01489 0.01032 -0.0622 0.9563 0.0128
-6.250 -0.3865 0.01441 0.00974 -0.0613 0.9509 0.0133
-6.000 -0.3614 0.01450 0.00977 -0.0605 0.9460 0.0136
-5.750 -0.3435 0.01211 0.00714 -0.0588 0.9405 0.0146
-5.500 -0.3200 0.01145 0.00642 -0.0579 0.9348 0.0152
-5.250 -0.2962 0.01093 0.00583 -0.0570 0.9300 0.0156
-5.000 -0.2713 0.01046 0.00531 -0.0564 0.9247 0.0162
-4.750 -0.2465 0.01000 0.00479 -0.0556 0.9191 0.0168
-4.500 -0.2214 0.00963 0.00435 -0.0549 0.9141 0.0176
-4.250 -0.1953 0.00931 0.00399 -0.0545 0.9079 0.0185
-4.000 -0.1695 0.00901 0.00363 -0.0539 0.9021 0.0189
-3.750 -0.1440 0.00856 0.00311 -0.0533 0.8956 0.0197
-3.500 -0.1182 0.00816 0.00262 -0.0527 0.8888 0.0212
-3.250 -0.0916 0.00790 0.00233 -0.0523 0.8818 0.0229
-3.000 -0.0649 0.00770 0.00208 -0.0519 0.8740 0.0251
-2.750 -0.0381 0.00745 0.00184 -0.0516 0.8653 0.0335
-2.500 -0.0122 0.00711 0.00162 -0.0511 0.8561 0.0734
-2.250 0.0139 0.00680 0.00146 -0.0507 0.8450 0.1231
-2.000 0.0399 0.00649 0.00133 -0.0504 0.8331 0.1831
-1.750 0.0657 0.00618 0.00121 -0.0500 0.8199 0.2577
-1.500 0.0911 0.00583 0.00111 -0.0496 0.8052 0.3485
-1.250 0.1159 0.00548 0.00103 -0.0491 0.7886 0.4582
-1.000 0.1411 0.00523 0.00098 -0.0485 0.7706 0.5436
-0.750 0.1653 0.00496 0.00096 -0.0478 0.7508 0.6456
-0.250 0.2141 0.00470 0.00096 -0.0460 0.7087 0.7828
0.250 0.2621 0.00456 0.00102 -0.0438 0.6659 0.9085
0.500 0.2959 0.00464 0.00107 -0.0449 0.6430 0.9493
0.750 0.3333 0.00478 0.00111 -0.0469 0.6181 0.9693
1.000 0.3704 0.00494 0.00115 -0.0489 0.5935 0.9811
1.250 0.4095 0.00510 0.00119 -0.0514 0.5676 0.9878
1.500 0.4462 0.00527 0.00123 -0.0533 0.5427 0.9937
2.000 0.5205 0.00557 0.00130 -0.0576 0.4917 1.0000
2.250 0.5441 0.00572 0.00136 -0.0568 0.4695 1.0000
2.500 0.5681 0.00587 0.00142 -0.0560 0.4483 1.0000
2.750 0.5920 0.00605 0.00150 -0.0553 0.4272 1.0000
3.000 0.6162 0.00621 0.00158 -0.0546 0.4072 1.0000
3.250 0.6402 0.00639 0.00168 -0.0538 0.3869 1.0000
3.500 0.6644 0.00657 0.00178 -0.0531 0.3679 1.0000
3.750 0.6887 0.00675 0.00190 -0.0524 0.3494 1.0000
4.000 0.7129 0.00695 0.00202 -0.0517 0.3316 1.0000
4.250 0.7372 0.00715 0.00215 -0.0511 0.3152 1.0000
4.500 0.7615 0.00735 0.00229 -0.0504 0.2990 1.0000
4.750 0.7859 0.00755 0.00245 -0.0498 0.2842 1.0000
5.000 0.8103 0.00775 0.00260 -0.0491 0.2699 1.0000
5.250 0.8346 0.00797 0.00277 -0.0485 0.2558 1.0000
5.500 0.8589 0.00819 0.00294 -0.0478 0.2427 1.0000
5.750 0.8831 0.00842 0.00314 -0.0472 0.2294 1.0000
6.000 0.9073 0.00865 0.00333 -0.0466 0.2155 1.0000
6.250 0.9313 0.00892 0.00354 -0.0459 0.1976 1.0000
6.500 0.9549 0.00924 0.00377 -0.0452 0.1783 1.0000
6.750 0.9781 0.00959 0.00404 -0.0445 0.1585 1.0000
7.000 1.0011 0.00996 0.00432 -0.0438 0.1381 1.0000
7.500 1.0464 0.01078 0.00497 -0.0422 0.1006 1.0000
7.750 1.0678 0.01131 0.00537 -0.0413 0.0793 1.0000
8.000 1.0881 0.01194 0.00588 -0.0402 0.0557 1.0000
8.250 1.1063 0.01277 0.00653 -0.0388 0.0296 1.0000
8.500 1.1232 0.01373 0.00735 -0.0371 0.0112 1.0000
8.750 1.1439 0.01430 0.00796 -0.0360 0.0086 1.0000
9.000 1.1643 0.01486 0.00855 -0.0349 0.0074 1.0000
9.250 1.1831 0.01558 0.00935 -0.0335 0.0065 1.0000
9.500 1.2032 0.01612 0.00997 -0.0323 0.0063 1.0000
9.750 1.2222 0.01673 0.01065 -0.0310 0.0059 1.0000
10.000 1.2404 0.01737 0.01135 -0.0297 0.0057 1.0000
10.250 1.2573 0.01806 0.01212 -0.0281 0.0055 1.0000
10.500 1.2728 0.01880 0.01293 -0.0264 0.0053 1.0000
10.750 1.2870 0.01958 0.01378 -0.0245 0.0051 1.0000
11.000 1.2955 0.02047 0.01475 -0.0216 0.0048 1.0000
11.250 1.3008 0.02146 0.01584 -0.0183 0.0047 1.0000
11.500 1.3031 0.02268 0.01718 -0.0149 0.0046 1.0000
11.750 1.2957 0.02459 0.01924 -0.0107 0.0045 1.0000
12.000 1.2986 0.02596 0.02073 -0.0081 0.0043 1.0000
12.250 1.3043 0.02723 0.02209 -0.0061 0.0043 1.0000
12.500 1.3090 0.02864 0.02359 -0.0042 0.0042 1.0000
12.750 1.3051 0.03081 0.02589 -0.0019 0.0042 1.0000
13.000 1.3049 0.03285 0.02805 -0.0003 0.0042 1.0000
13.250 1.3085 0.03469 0.02999 0.0007 0.0040 1.0000
13.500 1.3064 0.03722 0.03264 0.0016 0.0040 1.0000
13.750 1.3034 0.04002 0.03556 0.0021 0.0039 1.0000
14.000 1.2982 0.04327 0.03894 0.0022 0.0039 1.0000
14.250 1.2914 0.04694 0.04275 0.0018 0.0039 1.0000
14.500 1.2848 0.05085 0.04678 0.0010 0.0039 1.0000
14.750 1.2758 0.05529 0.05136 -0.0003 0.0038 1.0000
15.000 1.2668 0.05991 0.05611 -0.0018 0.0039 1.0000
15.250 1.2582 0.06477 0.06110 -0.0038 0.0038 1.0000
15.500 1.2469 0.07020 0.06667 -0.0062 0.0037 1.0000
15.750 1.2337 0.07610 0.07271 -0.0087 0.0038 1.0000
16.000 1.2211 0.08217 0.07891 -0.0116 0.0039 1.0000
16.250 1.2081 0.08852 0.08539 -0.0148 0.0038 1.0000
16.500 1.1942 0.09528 0.09228 -0.0183 0.0039 1.0000
16.750 1.1806 0.10217 0.09930 -0.0219 0.0039 1.0000
17.000 1.1652 0.10964 0.10689 -0.0259 0.0039 1.0000
17.250 1.1496 0.11747 0.11486 -0.0302 0.0038 1.0000
17.500 1.1377 0.12458 0.12207 -0.0342 0.0039 1.0000
17.750 1.1201 0.13330 0.13093 -0.0392 0.0039 1.0000
18.000 1.1095 0.14052 0.13825 -0.0434 0.0040 1.0000
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