S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 200,000 Max Cl/Cd: 57.55 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8065-il-200000-n5.txt Download as CSV file: xf-s8065-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8065 (11% version of S8064)
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5625 0.08864 0.08511 -0.0371 1.0000 0.0103
-11.000 -0.5802 0.07906 0.07560 -0.0424 1.0000 0.0100
-10.750 -0.6129 0.06446 0.06090 -0.0533 1.0000 0.0096
-10.500 -0.6384 0.05706 0.05336 -0.0588 1.0000 0.0095
-10.250 -0.6610 0.05205 0.04818 -0.0606 1.0000 0.0094
-10.000 -0.6847 0.04811 0.04404 -0.0596 1.0000 0.0094
-9.750 -0.7092 0.04583 0.04163 -0.0551 1.0000 0.0093
-9.500 -0.7262 0.04295 0.03850 -0.0515 0.9952 0.0092
-9.250 -0.7243 0.03807 0.03307 -0.0518 0.9868 0.0092
-9.000 -0.7136 0.03409 0.02856 -0.0520 0.9816 0.0092
-8.750 -0.6988 0.03108 0.02509 -0.0518 0.9765 0.0092
-8.500 -0.6784 0.02846 0.02205 -0.0519 0.9729 0.0094
-8.250 -0.6563 0.02631 0.01956 -0.0520 0.9696 0.0097
-8.000 -0.6352 0.02459 0.01753 -0.0515 0.9654 0.0100
-7.750 -0.6111 0.02305 0.01576 -0.0515 0.9621 0.0103
-7.500 -0.5855 0.02172 0.01422 -0.0517 0.9593 0.0107
-7.250 -0.5618 0.02052 0.01288 -0.0515 0.9562 0.0112
-7.000 -0.5411 0.01967 0.01195 -0.0508 0.9517 0.0121
-6.750 -0.5164 0.01900 0.01118 -0.0507 0.9483 0.0136
-6.500 -0.4911 0.01820 0.01025 -0.0506 0.9454 0.0152
-6.250 -0.4687 0.01737 0.00934 -0.0500 0.9420 0.0168
-6.000 -0.4477 0.01675 0.00862 -0.0489 0.9375 0.0198
-5.750 -0.4248 0.01605 0.00788 -0.0482 0.9338 0.0269
-5.500 -0.3997 0.01548 0.00730 -0.0480 0.9309 0.0395
-5.250 -0.3773 0.01502 0.00693 -0.0473 0.9271 0.0609
-5.000 -0.3559 0.01455 0.00659 -0.0465 0.9227 0.0886
-4.750 -0.3323 0.01408 0.00622 -0.0459 0.9192 0.1174
-4.500 -0.3078 0.01362 0.00586 -0.0456 0.9163 0.1540
-4.250 -0.2872 0.01317 0.00557 -0.0445 0.9118 0.2035
-4.000 -0.2669 0.01262 0.00530 -0.0435 0.9074 0.2747
-3.750 -0.2460 0.01204 0.00506 -0.0425 0.9038 0.3633
-3.500 -0.2247 0.01156 0.00489 -0.0413 0.9005 0.4500
-3.250 -0.2049 0.01126 0.00480 -0.0399 0.8952 0.5180
-3.000 -0.1819 0.01100 0.00472 -0.0388 0.8913 0.5757
-2.750 -0.1572 0.01081 0.00467 -0.0379 0.8882 0.6255
-2.500 -0.1340 0.01073 0.00471 -0.0368 0.8839 0.6682
-2.250 -0.1099 0.01070 0.00472 -0.0358 0.8792 0.7028
-2.000 -0.0839 0.01067 0.00469 -0.0351 0.8756 0.7305
-1.750 -0.0572 0.01064 0.00465 -0.0346 0.8727 0.7543
-1.500 -0.0341 0.01067 0.00470 -0.0335 0.8667 0.7744
-1.250 -0.0084 0.01066 0.00468 -0.0328 0.8624 0.7926
-1.000 0.0187 0.01062 0.00463 -0.0323 0.8592 0.8076
-0.750 0.0432 0.01064 0.00466 -0.0315 0.8535 0.8200
-0.500 0.0694 0.01061 0.00462 -0.0310 0.8486 0.8309
-0.250 0.0968 0.01055 0.00454 -0.0307 0.8449 0.8415
0.000 0.1220 0.01056 0.00457 -0.0301 0.8389 0.8513
0.250 0.1489 0.01052 0.00454 -0.0297 0.8335 0.8602
0.500 0.1767 0.01044 0.00445 -0.0294 0.8296 0.8697
0.750 0.2024 0.01045 0.00451 -0.0289 0.8220 0.8780
1.000 0.2305 0.01038 0.00445 -0.0288 0.8167 0.8865
1.250 0.2573 0.01036 0.00447 -0.0285 0.8090 0.8951
1.500 0.2867 0.01027 0.00440 -0.0286 0.8023 0.9027
1.750 0.3140 0.01023 0.00441 -0.0284 0.7927 0.9116
2.000 0.3451 0.01015 0.00437 -0.0289 0.7833 0.9184
2.250 0.3746 0.01005 0.00430 -0.0290 0.7723 0.9270
2.500 0.4075 0.00997 0.00425 -0.0298 0.7581 0.9331
2.750 0.4377 0.00990 0.00422 -0.0301 0.7404 0.9413
3.000 0.4720 0.00982 0.00411 -0.0312 0.7183 0.9468
3.250 0.5038 0.00980 0.00404 -0.0318 0.6896 0.9541
3.500 0.5364 0.00988 0.00403 -0.0326 0.6514 0.9604
3.750 0.5671 0.01007 0.00407 -0.0331 0.6059 0.9679
4.000 0.5979 0.01039 0.00418 -0.0338 0.5492 0.9748
4.250 0.6253 0.01092 0.00439 -0.0341 0.4745 0.9836
4.500 0.6531 0.01170 0.00475 -0.0349 0.3777 0.9917
4.750 0.6797 0.01265 0.00522 -0.0358 0.2793 1.0000
5.000 0.6892 0.01330 0.00559 -0.0328 0.2212 1.0000
5.250 0.7010 0.01392 0.00597 -0.0302 0.1737 1.0000
5.500 0.7148 0.01452 0.00640 -0.0280 0.1365 1.0000
5.750 0.7302 0.01507 0.00684 -0.0260 0.1117 1.0000
6.000 0.7466 0.01560 0.00730 -0.0242 0.0926 1.0000
6.250 0.7636 0.01614 0.00779 -0.0224 0.0787 1.0000
6.500 0.7812 0.01667 0.00833 -0.0208 0.0685 1.0000
6.750 0.7982 0.01729 0.00895 -0.0191 0.0610 1.0000
7.000 0.8166 0.01782 0.00952 -0.0177 0.0535 1.0000
7.250 0.8347 0.01838 0.01009 -0.0163 0.0459 1.0000
7.500 0.8521 0.01901 0.01070 -0.0148 0.0394 1.0000
7.750 0.8704 0.01959 0.01137 -0.0134 0.0349 1.0000
8.000 0.8872 0.02029 0.01206 -0.0119 0.0298 1.0000
8.250 0.9044 0.02097 0.01286 -0.0104 0.0260 1.0000
8.500 0.9200 0.02176 0.01369 -0.0087 0.0227 1.0000
8.750 0.9324 0.02277 0.01478 -0.0065 0.0206 1.0000
9.000 0.9460 0.02372 0.01584 -0.0044 0.0189 1.0000
9.250 0.9595 0.02470 0.01692 -0.0025 0.0175 1.0000
9.500 0.9723 0.02575 0.01804 -0.0006 0.0164 1.0000
9.750 0.9827 0.02714 0.01948 0.0014 0.0155 1.0000
10.000 0.9972 0.02824 0.02080 0.0030 0.0146 1.0000
10.250 1.0100 0.02953 0.02225 0.0046 0.0138 1.0000
10.500 1.0221 0.03082 0.02370 0.0063 0.0131 1.0000
10.750 1.0325 0.03226 0.02528 0.0080 0.0126 1.0000
11.000 1.0416 0.03382 0.02700 0.0097 0.0122 1.0000
11.250 1.0489 0.03543 0.02874 0.0115 0.0118 1.0000
11.500 1.0545 0.03725 0.03072 0.0132 0.0116 1.0000
11.750 1.0573 0.03948 0.03314 0.0150 0.0114 1.0000
12.000 1.0563 0.04214 0.03602 0.0169 0.0111 1.0000
12.250 1.0535 0.04488 0.03905 0.0186 0.0110 1.0000
12.500 1.0474 0.04798 0.04242 0.0201 0.0109 1.0000
12.750 1.0383 0.05143 0.04614 0.0211 0.0108 1.0000
13.000 1.0272 0.05521 0.05017 0.0216 0.0108 1.0000
13.250 1.0116 0.05979 0.05502 0.0213 0.0107 1.0000
13.500 0.9937 0.06502 0.06050 0.0200 0.0107 1.0000
13.750 0.9753 0.07085 0.06655 0.0177 0.0107 1.0000
14.000 0.9544 0.07779 0.07370 0.0140 0.0107 1.0000
14.250 0.9331 0.08571 0.08180 0.0092 0.0108 1.0000
14.500 0.9095 0.09530 0.09155 0.0029 0.0109 1.0000
14.750 0.8854 0.10614 0.10253 -0.0041 0.0110 1.0000
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