SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7084 (9.6%) (sd7084-il) Reynolds number: 500,000 Max Cl/Cd: 83.53 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7084-il-500000-n5.txt Download as CSV file: xf-sd7084-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4719 0.08441 0.08217 -0.0312 1.0000 0.0084
-9.500 -0.4794 0.07901 0.07681 -0.0340 1.0000 0.0088
-9.250 -0.4919 0.07286 0.07070 -0.0375 1.0000 0.0088
-9.000 -0.5174 0.06498 0.06291 -0.0431 1.0000 0.0086
-8.750 -0.5710 0.05198 0.04982 -0.0504 0.9986 0.0083
-8.500 -0.6008 0.02960 0.02615 -0.0606 0.9843 0.0090
-8.250 -0.5831 0.02560 0.02163 -0.0614 0.9792 0.0096
-8.000 -0.5611 0.02301 0.01863 -0.0618 0.9745 0.0101
-7.750 -0.5350 0.02124 0.01653 -0.0624 0.9712 0.0105
-7.500 -0.5089 0.02047 0.01556 -0.0625 0.9670 0.0108
-7.250 -0.4884 0.01834 0.01313 -0.0620 0.9615 0.0116
-7.000 -0.4624 0.01741 0.01207 -0.0620 0.9576 0.0120
-6.750 -0.4386 0.01660 0.01114 -0.0614 0.9523 0.0124
-6.500 -0.4144 0.01585 0.01027 -0.0609 0.9469 0.0128
-6.000 -0.3661 0.01437 0.00852 -0.0595 0.9365 0.0136
-5.750 -0.3416 0.01379 0.00784 -0.0588 0.9313 0.0143
-5.500 -0.3168 0.01326 0.00722 -0.0582 0.9262 0.0149
-5.250 -0.2923 0.01273 0.00660 -0.0575 0.9200 0.0154
-5.000 -0.2677 0.01221 0.00600 -0.0567 0.9148 0.0157
-4.750 -0.2427 0.01178 0.00550 -0.0561 0.9079 0.0160
-4.500 -0.2187 0.01112 0.00473 -0.0553 0.9017 0.0167
-4.250 -0.1936 0.01066 0.00422 -0.0547 0.8948 0.0176
-4.000 -0.1680 0.01032 0.00382 -0.0541 0.8881 0.0183
-3.750 -0.1420 0.01003 0.00348 -0.0536 0.8806 0.0192
-3.500 -0.1158 0.00978 0.00317 -0.0532 0.8730 0.0204
-3.250 -0.0894 0.00956 0.00289 -0.0528 0.8640 0.0219
-3.000 -0.0630 0.00932 0.00260 -0.0523 0.8548 0.0244
-2.750 -0.0367 0.00909 0.00236 -0.0518 0.8445 0.0314
-2.500 -0.0105 0.00883 0.00215 -0.0514 0.8327 0.0526
-2.250 0.0157 0.00859 0.00196 -0.0510 0.8194 0.0795
-2.000 0.0416 0.00835 0.00179 -0.0506 0.8040 0.1172
-1.750 0.0671 0.00805 0.00164 -0.0501 0.7866 0.1773
-1.500 0.0919 0.00771 0.00151 -0.0496 0.7665 0.2633
-1.250 0.1157 0.00728 0.00141 -0.0490 0.7457 0.3865
-1.000 0.1405 0.00704 0.00134 -0.0484 0.7239 0.4685
-0.750 0.1645 0.00681 0.00131 -0.0476 0.7024 0.5574
-0.500 0.1876 0.00656 0.00130 -0.0466 0.6804 0.6574
-0.250 0.2115 0.00645 0.00130 -0.0456 0.6588 0.7237
0.000 0.2352 0.00636 0.00132 -0.0445 0.6368 0.7853
0.250 0.2593 0.00633 0.00135 -0.0434 0.6149 0.8381
0.500 0.2855 0.00633 0.00139 -0.0428 0.5926 0.8899
0.750 0.3220 0.00644 0.00145 -0.0445 0.5687 0.9340
1.000 0.3623 0.00660 0.00149 -0.0471 0.5439 0.9584
1.250 0.3994 0.00676 0.00153 -0.0492 0.5201 0.9740
1.500 0.4343 0.00693 0.00158 -0.0508 0.4966 0.9852
1.750 0.4690 0.00711 0.00164 -0.0523 0.4733 0.9933
2.000 0.5056 0.00728 0.00170 -0.0544 0.4497 0.9995
2.250 0.5310 0.00745 0.00177 -0.0540 0.4301 1.0000
2.500 0.5549 0.00762 0.00185 -0.0532 0.4111 1.0000
2.750 0.5786 0.00781 0.00196 -0.0524 0.3919 1.0000
3.000 0.6027 0.00799 0.00206 -0.0517 0.3743 1.0000
3.250 0.6267 0.00819 0.00218 -0.0510 0.3559 1.0000
3.500 0.6507 0.00839 0.00230 -0.0503 0.3395 1.0000
3.750 0.6747 0.00860 0.00245 -0.0496 0.3232 1.0000
4.000 0.6988 0.00880 0.00260 -0.0489 0.3083 1.0000
4.250 0.7229 0.00902 0.00276 -0.0482 0.2939 1.0000
4.500 0.7470 0.00923 0.00293 -0.0475 0.2801 1.0000
4.750 0.7713 0.00945 0.00313 -0.0468 0.2673 1.0000
5.000 0.7955 0.00968 0.00332 -0.0462 0.2546 1.0000
5.250 0.8198 0.00990 0.00353 -0.0456 0.2431 1.0000
5.500 0.8440 0.01015 0.00374 -0.0450 0.2311 1.0000
5.750 0.8681 0.01041 0.00397 -0.0443 0.2189 1.0000
6.000 0.8921 0.01068 0.00423 -0.0437 0.2066 1.0000
6.250 0.9160 0.01097 0.00449 -0.0431 0.1936 1.0000
6.500 0.9395 0.01128 0.00477 -0.0424 0.1777 1.0000
6.750 0.9622 0.01169 0.00508 -0.0416 0.1562 1.0000
7.000 0.9846 0.01212 0.00543 -0.0408 0.1350 1.0000
7.250 1.0062 0.01263 0.00584 -0.0399 0.1124 1.0000
7.500 1.0270 0.01321 0.00629 -0.0390 0.0885 1.0000
7.750 1.0467 0.01389 0.00683 -0.0379 0.0630 1.0000
8.000 1.0656 0.01465 0.00744 -0.0366 0.0402 1.0000
8.250 1.0849 0.01534 0.00807 -0.0354 0.0251 1.0000
8.500 1.1037 0.01606 0.00874 -0.0342 0.0145 1.0000
8.750 1.1229 0.01672 0.00942 -0.0329 0.0096 1.0000
9.000 1.1417 0.01740 0.01014 -0.0316 0.0073 1.0000
9.250 1.1612 0.01798 0.01080 -0.0304 0.0067 1.0000
9.500 1.1796 0.01862 0.01153 -0.0291 0.0060 1.0000
9.750 1.1969 0.01931 0.01229 -0.0276 0.0055 1.0000
10.000 1.2124 0.02011 0.01318 -0.0259 0.0051 1.0000
10.250 1.2255 0.02102 0.01419 -0.0239 0.0046 1.0000
10.500 1.2381 0.02176 0.01502 -0.0217 0.0044 1.0000
10.750 1.2483 0.02259 0.01597 -0.0193 0.0043 1.0000
11.000 1.2572 0.02350 0.01698 -0.0168 0.0041 1.0000
11.250 1.2653 0.02449 0.01808 -0.0143 0.0039 1.0000
11.500 1.2719 0.02562 0.01932 -0.0119 0.0039 1.0000
11.750 1.2781 0.02682 0.02062 -0.0097 0.0038 1.0000
12.000 1.2818 0.02824 0.02217 -0.0075 0.0037 1.0000
12.250 1.2851 0.02977 0.02381 -0.0055 0.0036 1.0000
12.500 1.2874 0.03147 0.02563 -0.0037 0.0035 1.0000
12.750 1.2883 0.03339 0.02766 -0.0022 0.0034 1.0000
13.000 1.2876 0.03560 0.03000 -0.0010 0.0034 1.0000
13.250 1.2858 0.03809 0.03261 -0.0001 0.0033 1.0000
13.500 1.2827 0.04091 0.03556 0.0003 0.0033 1.0000
13.750 1.2796 0.04395 0.03876 0.0002 0.0032 1.0000
14.000 1.2744 0.04748 0.04241 -0.0003 0.0031 1.0000
14.250 1.2669 0.05155 0.04662 -0.0013 0.0031 1.0000
14.500 1.2594 0.05588 0.05110 -0.0027 0.0031 1.0000
14.750 1.2493 0.06080 0.05615 -0.0046 0.0030 1.0000
15.000 1.2402 0.06583 0.06132 -0.0067 0.0030 1.0000
15.250 1.2305 0.07113 0.06675 -0.0091 0.0030 1.0000
15.500 1.2177 0.07710 0.07286 -0.0119 0.0030 1.0000
15.750 1.2059 0.08312 0.07901 -0.0147 0.0030 1.0000
16.000 1.1920 0.08963 0.08565 -0.0179 0.0029 1.0000
16.250 1.1809 0.09587 0.09201 -0.0210 0.0030 1.0000
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Polar data table (+)
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