SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 200,000 Max Cl/Cd: 62.76 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd5060-il-200000-n5.txt Download as CSV file: xf-sd5060-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD5060 (9.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5691 0.08248 0.07895 -0.0194 1.0000 0.0169
-10.000 -0.5951 0.07215 0.06867 -0.0257 1.0000 0.0167
-9.750 -0.6247 0.06074 0.05726 -0.0344 1.0000 0.0162
-9.500 -0.6554 0.04961 0.04597 -0.0469 1.0000 0.0159
-9.250 -0.6701 0.04320 0.03917 -0.0514 1.0000 0.0159
-9.000 -0.6729 0.03816 0.03365 -0.0533 1.0000 0.0162
-8.750 -0.6664 0.03425 0.02925 -0.0538 1.0000 0.0164
-8.500 -0.6540 0.03122 0.02574 -0.0538 1.0000 0.0167
-8.250 -0.6393 0.02845 0.02259 -0.0535 1.0000 0.0171
-8.000 -0.6226 0.02620 0.02012 -0.0530 1.0000 0.0176
-7.750 -0.6040 0.02469 0.01847 -0.0523 1.0000 0.0182
-7.500 -0.5852 0.02363 0.01729 -0.0514 1.0000 0.0191
-7.250 -0.5676 0.02254 0.01605 -0.0501 1.0000 0.0201
-6.750 -0.5054 0.01978 0.01282 -0.0526 0.9864 0.0217
-6.500 -0.4724 0.01866 0.01151 -0.0540 0.9793 0.0224
-6.250 -0.4405 0.01737 0.01013 -0.0554 0.9717 0.0234
-6.000 -0.4089 0.01656 0.00925 -0.0565 0.9636 0.0253
-5.750 -0.3761 0.01587 0.00846 -0.0578 0.9563 0.0272
-5.500 -0.3460 0.01521 0.00769 -0.0583 0.9470 0.0286
-5.250 -0.3156 0.01457 0.00694 -0.0589 0.9387 0.0305
-5.000 -0.2867 0.01400 0.00630 -0.0591 0.9294 0.0337
-4.750 -0.2589 0.01355 0.00576 -0.0590 0.9198 0.0390
-4.500 -0.2316 0.01299 0.00526 -0.0588 0.9109 0.0556
-4.250 -0.2053 0.01251 0.00489 -0.0585 0.9010 0.0836
-4.000 -0.1789 0.01218 0.00459 -0.0582 0.8914 0.1084
-3.750 -0.1525 0.01191 0.00435 -0.0577 0.8827 0.1332
-3.500 -0.1261 0.01167 0.00415 -0.0574 0.8727 0.1588
-3.250 -0.0997 0.01143 0.00398 -0.0570 0.8633 0.1886
-3.000 -0.0734 0.01121 0.00379 -0.0565 0.8545 0.2165
-2.750 -0.0467 0.01101 0.00362 -0.0561 0.8444 0.2399
-2.500 -0.0201 0.01082 0.00347 -0.0557 0.8352 0.2660
-2.250 0.0064 0.01063 0.00332 -0.0553 0.8259 0.2959
-2.000 0.0333 0.01044 0.00319 -0.0550 0.8158 0.3282
-1.750 0.0599 0.01026 0.00308 -0.0546 0.8063 0.3639
-1.500 0.0865 0.01008 0.00298 -0.0541 0.7965 0.4037
-1.250 0.1132 0.00989 0.00291 -0.0538 0.7860 0.4487
-1.000 0.1395 0.00970 0.00285 -0.0533 0.7757 0.4993
-0.750 0.1655 0.00951 0.00280 -0.0526 0.7655 0.5552
-0.500 0.1912 0.00931 0.00278 -0.0519 0.7539 0.6162
-0.250 0.2162 0.00912 0.00277 -0.0509 0.7423 0.6809
0.000 0.2403 0.00893 0.00277 -0.0496 0.7305 0.7512
0.250 0.2641 0.00877 0.00276 -0.0481 0.7181 0.8247
0.500 0.2936 0.00865 0.00271 -0.0477 0.7046 0.9045
0.750 0.3356 0.00859 0.00261 -0.0503 0.6887 0.9838
1.000 0.3650 0.00866 0.00257 -0.0505 0.6725 1.0000
1.250 0.3916 0.00875 0.00256 -0.0501 0.6561 1.0000
1.500 0.4182 0.00885 0.00257 -0.0497 0.6391 1.0000
1.750 0.4449 0.00897 0.00259 -0.0493 0.6215 1.0000
2.000 0.4715 0.00910 0.00262 -0.0489 0.6027 1.0000
2.250 0.4982 0.00924 0.00267 -0.0485 0.5822 1.0000
2.500 0.5246 0.00941 0.00273 -0.0481 0.5607 1.0000
2.750 0.5511 0.00959 0.00283 -0.0478 0.5365 1.0000
3.000 0.5774 0.00980 0.00293 -0.0474 0.5118 1.0000
3.250 0.6035 0.01003 0.00305 -0.0470 0.4852 1.0000
3.500 0.6294 0.01029 0.00320 -0.0466 0.4572 1.0000
3.750 0.6551 0.01058 0.00337 -0.0462 0.4275 1.0000
4.000 0.6807 0.01091 0.00357 -0.0458 0.3963 1.0000
4.250 0.7060 0.01127 0.00380 -0.0454 0.3646 1.0000
4.500 0.7312 0.01165 0.00408 -0.0450 0.3347 1.0000
4.750 0.7562 0.01206 0.00436 -0.0446 0.3057 1.0000
5.000 0.7810 0.01249 0.00468 -0.0442 0.2780 1.0000
5.250 0.8058 0.01293 0.00502 -0.0438 0.2540 1.0000
5.500 0.8307 0.01336 0.00540 -0.0434 0.2327 1.0000
5.750 0.8552 0.01383 0.00579 -0.0430 0.2132 1.0000
6.000 0.8798 0.01427 0.00620 -0.0426 0.1963 1.0000
6.250 0.9043 0.01473 0.00662 -0.0422 0.1815 1.0000
6.500 0.9286 0.01520 0.00709 -0.0417 0.1679 1.0000
6.750 0.9526 0.01570 0.00757 -0.0412 0.1557 1.0000
7.000 0.9766 0.01618 0.00805 -0.0408 0.1445 1.0000
7.250 1.0005 0.01666 0.00856 -0.0403 0.1345 1.0000
7.500 1.0239 0.01719 0.00912 -0.0397 0.1256 1.0000
7.750 1.0467 0.01775 0.00969 -0.0391 0.1164 1.0000
8.000 1.0701 0.01826 0.01026 -0.0386 0.1079 1.0000
8.250 1.0923 0.01886 0.01088 -0.0379 0.1004 1.0000
8.500 1.1148 0.01942 0.01151 -0.0373 0.0927 1.0000
8.750 1.1364 0.02005 0.01220 -0.0366 0.0858 1.0000
9.000 1.1575 0.02070 0.01289 -0.0358 0.0784 1.0000
9.250 1.1785 0.02136 0.01364 -0.0350 0.0719 1.0000
9.500 1.1979 0.02214 0.01443 -0.0341 0.0652 1.0000
9.750 1.2177 0.02285 0.01525 -0.0332 0.0591 1.0000
10.000 1.2352 0.02373 0.01613 -0.0321 0.0526 1.0000
10.250 1.2535 0.02451 0.01701 -0.0312 0.0457 1.0000
10.500 1.2697 0.02543 0.01799 -0.0300 0.0398 1.0000
10.750 1.2839 0.02647 0.01903 -0.0287 0.0342 1.0000
11.000 1.2975 0.02746 0.02015 -0.0272 0.0305 1.0000
11.250 1.3069 0.02860 0.02135 -0.0252 0.0271 1.0000
11.500 1.3138 0.02990 0.02275 -0.0232 0.0246 1.0000
11.750 1.3211 0.03123 0.02422 -0.0214 0.0220 1.0000
12.000 1.3248 0.03291 0.02597 -0.0197 0.0197 1.0000
12.250 1.3278 0.03473 0.02795 -0.0182 0.0179 1.0000
12.500 1.3306 0.03665 0.03001 -0.0170 0.0162 1.0000
12.750 1.3307 0.03893 0.03240 -0.0160 0.0149 1.0000
13.000 1.3278 0.04165 0.03524 -0.0154 0.0139 1.0000
13.250 1.3268 0.04437 0.03815 -0.0151 0.0129 1.0000
13.500 1.3230 0.04755 0.04149 -0.0153 0.0124 1.0000
13.750 1.3179 0.05110 0.04520 -0.0159 0.0118 1.0000
14.000 1.3107 0.05516 0.04941 -0.0170 0.0114 1.0000
14.250 1.3016 0.05974 0.05416 -0.0186 0.0112 1.0000
14.500 1.2897 0.06503 0.05960 -0.0209 0.0109 1.0000
14.750 1.2765 0.07086 0.06560 -0.0237 0.0108 1.0000
15.000 1.2604 0.07754 0.07245 -0.0272 0.0107 1.0000
15.250 1.2441 0.08466 0.07973 -0.0310 0.0106 1.0000
15.500 1.2264 0.09241 0.08765 -0.0353 0.0105 1.0000
15.750 1.2096 0.10031 0.09571 -0.0398 0.0106 1.0000
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