NREL's S805A Airfoil (s805a-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S805A Airfoil (s805a-nr) Reynolds number: 500,000 Max Cl/Cd: 89.86 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s805a-nr-500000-n5.txt Download as CSV file: xf-s805a-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S805A Airfoil
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5817 0.05740 0.05497 -0.0660 1.0000 0.0082
-10.500 -0.6238 0.05102 0.04842 -0.0648 1.0000 0.0082
-10.250 -0.6897 0.03875 0.03546 -0.0631 0.9866 0.0084
-10.000 -0.7025 0.03186 0.02784 -0.0620 0.9760 0.0087
-9.750 -0.6904 0.02876 0.02431 -0.0618 0.9671 0.0089
-9.500 -0.6753 0.02599 0.02118 -0.0616 0.9562 0.0091
-9.250 -0.6537 0.02472 0.01978 -0.0617 0.9403 0.0094
-9.000 -0.6284 0.02335 0.01820 -0.0624 0.9150 0.0096
-8.750 -0.6031 0.02245 0.01707 -0.0626 0.8752 0.0099
-8.500 -0.5842 0.02156 0.01587 -0.0614 0.8387 0.0102
-8.250 -0.5650 0.02089 0.01495 -0.0602 0.8121 0.0106
-8.000 -0.5449 0.02009 0.01392 -0.0591 0.7922 0.0111
-7.750 -0.5240 0.01921 0.01280 -0.0581 0.7757 0.0115
-7.500 -0.5023 0.01836 0.01175 -0.0573 0.7616 0.0118
-7.250 -0.4799 0.01767 0.01087 -0.0565 0.7489 0.0120
-7.000 -0.4570 0.01708 0.01012 -0.0558 0.7374 0.0122
-6.750 -0.4358 0.01605 0.00897 -0.0550 0.7273 0.0126
-6.500 -0.4137 0.01541 0.00824 -0.0542 0.7184 0.0130
-6.250 -0.3908 0.01490 0.00766 -0.0536 0.7101 0.0134
-6.000 -0.3671 0.01453 0.00723 -0.0531 0.7030 0.0140
-5.750 -0.3435 0.01411 0.00673 -0.0525 0.6959 0.0146
-5.500 -0.3202 0.01369 0.00623 -0.0519 0.6895 0.0151
-5.250 -0.2965 0.01327 0.00574 -0.0513 0.6832 0.0156
-5.000 -0.2726 0.01291 0.00530 -0.0507 0.6772 0.0160
-4.750 -0.2480 0.01260 0.00492 -0.0503 0.6720 0.0164
-4.500 -0.2245 0.01214 0.00442 -0.0497 0.6669 0.0172
-4.250 -0.1998 0.01184 0.00406 -0.0493 0.6623 0.0181
-4.000 -0.1743 0.01159 0.00378 -0.0490 0.6581 0.0193
-3.750 -0.1484 0.01137 0.00351 -0.0488 0.6537 0.0208
-3.500 -0.1226 0.01117 0.00325 -0.0485 0.6493 0.0227
-3.250 -0.0969 0.01096 0.00301 -0.0483 0.6455 0.0262
-3.000 -0.0711 0.01070 0.00282 -0.0481 0.6416 0.0405
-2.750 -0.0456 0.01040 0.00263 -0.0479 0.6379 0.0738
-2.500 -0.0213 0.00998 0.00244 -0.0476 0.6345 0.1416
-2.000 0.0216 0.00839 0.00195 -0.0465 0.6283 0.4558
-1.750 0.0421 0.00760 0.00186 -0.0455 0.6249 0.6436
-1.500 0.0678 0.00754 0.00197 -0.0450 0.6215 0.7109
-1.250 0.0942 0.00762 0.00212 -0.0445 0.6186 0.7482
-1.000 0.1216 0.00772 0.00219 -0.0444 0.6160 0.7636
-0.750 0.1502 0.00774 0.00218 -0.0446 0.6132 0.7693
-0.500 0.1787 0.00776 0.00218 -0.0448 0.6102 0.7724
-0.250 0.2071 0.00779 0.00217 -0.0450 0.6071 0.7757
0.000 0.2356 0.00783 0.00216 -0.0452 0.6044 0.7793
0.250 0.2642 0.00788 0.00215 -0.0455 0.6020 0.7828
0.500 0.2926 0.00790 0.00218 -0.0457 0.5994 0.7854
0.750 0.3210 0.00793 0.00222 -0.0459 0.5965 0.7885
1.000 0.3494 0.00797 0.00225 -0.0461 0.5937 0.7919
1.250 0.3779 0.00802 0.00228 -0.0464 0.5910 0.7955
1.500 0.4063 0.00807 0.00231 -0.0466 0.5884 0.7986
1.750 0.4345 0.00813 0.00236 -0.0468 0.5858 0.8008
2.000 0.4628 0.00816 0.00243 -0.0470 0.5827 0.8033
2.250 0.4910 0.00819 0.00249 -0.0472 0.5788 0.8060
2.500 0.5190 0.00824 0.00253 -0.0474 0.5745 0.8088
2.750 0.5471 0.00830 0.00258 -0.0476 0.5697 0.8116
3.000 0.5749 0.00832 0.00264 -0.0477 0.5632 0.8141
3.250 0.6019 0.00838 0.00269 -0.0476 0.5564 0.8165
3.500 0.6294 0.00841 0.00276 -0.0477 0.5482 0.8191
3.750 0.6566 0.00847 0.00284 -0.0477 0.5406 0.8218
4.000 0.6840 0.00852 0.00291 -0.0477 0.5314 0.8247
4.250 0.7113 0.00859 0.00299 -0.0478 0.5220 0.8277
4.500 0.7376 0.00866 0.00309 -0.0476 0.5104 0.8302
4.750 0.7638 0.00875 0.00320 -0.0474 0.4973 0.8328
5.000 0.7898 0.00886 0.00332 -0.0472 0.4823 0.8357
5.250 0.8141 0.00906 0.00344 -0.0467 0.4540 0.8388
5.500 0.8330 0.00958 0.00370 -0.0454 0.3921 0.8422
5.750 0.8481 0.01036 0.00416 -0.0434 0.3231 0.8454
6.000 0.8647 0.01105 0.00462 -0.0418 0.2688 0.8490
6.250 0.8829 0.01165 0.00505 -0.0404 0.2276 0.8528
6.500 0.9007 0.01227 0.00549 -0.0391 0.1891 0.8566
6.750 0.9188 0.01279 0.00591 -0.0377 0.1602 0.8599
7.000 0.9368 0.01327 0.00633 -0.0362 0.1377 0.8636
7.250 0.9552 0.01373 0.00674 -0.0349 0.1188 0.8679
7.750 0.9891 0.01468 0.00762 -0.0317 0.0880 0.8766
8.000 1.0041 0.01513 0.00805 -0.0297 0.0763 0.8815
8.250 1.0183 0.01557 0.00849 -0.0277 0.0671 0.8868
8.500 1.0305 0.01605 0.00899 -0.0252 0.0591 0.8925
8.750 1.0430 0.01657 0.00952 -0.0229 0.0516 0.8996
9.000 1.0550 0.01708 0.01008 -0.0206 0.0455 0.9072
9.500 1.0775 0.01819 0.01128 -0.0160 0.0364 0.9282
9.750 1.0887 0.01880 0.01194 -0.0139 0.0329 0.9464
10.250 1.1234 0.02021 0.01346 -0.0127 0.0274 1.0000
10.500 1.1364 0.02104 0.01432 -0.0115 0.0254 1.0000
10.750 1.1483 0.02197 0.01528 -0.0102 0.0231 1.0000
11.000 1.1617 0.02284 0.01621 -0.0092 0.0214 1.0000
11.250 1.1731 0.02386 0.01725 -0.0081 0.0191 1.0000
11.500 1.1841 0.02496 0.01840 -0.0070 0.0168 1.0000
11.750 1.1940 0.02618 0.01963 -0.0060 0.0139 1.0000
12.000 1.2042 0.02741 0.02091 -0.0050 0.0123 1.0000
12.250 1.2122 0.02886 0.02238 -0.0041 0.0100 1.0000
12.500 1.2217 0.03023 0.02383 -0.0032 0.0093 1.0000
12.750 1.2289 0.03181 0.02546 -0.0024 0.0081 1.0000
13.000 1.2359 0.03346 0.02717 -0.0016 0.0075 1.0000
13.250 1.2428 0.03516 0.02894 -0.0009 0.0071 1.0000
13.500 1.2494 0.03692 0.03080 -0.0003 0.0067 1.0000
13.750 1.2558 0.03873 0.03270 0.0002 0.0064 1.0000
14.000 1.2613 0.04067 0.03473 0.0006 0.0061 1.0000
14.250 1.2658 0.04274 0.03690 0.0010 0.0059 1.0000
14.500 1.2693 0.04497 0.03922 0.0013 0.0056 1.0000
14.750 1.2725 0.04730 0.04166 0.0015 0.0055 1.0000
15.000 1.2731 0.04997 0.04442 0.0016 0.0053 1.0000
15.250 1.2735 0.05275 0.04731 0.0015 0.0051 1.0000
15.500 1.2706 0.05602 0.05070 0.0012 0.0049 1.0000
15.750 1.2697 0.05916 0.05395 0.0008 0.0049 1.0000
16.000 1.2705 0.06217 0.05707 0.0003 0.0048 1.0000
16.250 1.2709 0.06534 0.06036 -0.0004 0.0047 1.0000
16.500 1.2671 0.06918 0.06434 -0.0014 0.0046 1.0000
16.750 1.2656 0.07279 0.06807 -0.0024 0.0045 1.0000
17.000 1.2610 0.07699 0.07240 -0.0038 0.0044 1.0000
17.250 1.2568 0.08126 0.07679 -0.0054 0.0043 1.0000
17.500 1.2505 0.08601 0.08167 -0.0072 0.0042 1.0000
17.750 1.2430 0.09110 0.08691 -0.0094 0.0042 1.0000
18.000 1.2327 0.09685 0.09280 -0.0120 0.0042 1.0000
18.250 1.2232 0.10266 0.09875 -0.0148 0.0041 1.0000
18.500 1.2121 0.10894 0.10517 -0.0180 0.0041 1.0000
18.750 1.1998 0.11558 0.11195 -0.0215 0.0041 1.0000
19.000 1.1875 0.12244 0.11896 -0.0252 0.0040 1.0000
19.250 1.1733 0.12987 0.12653 -0.0294 0.0040 1.0000
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