NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S810 Airfoil (s810-nr) Reynolds number: 500,000 Max Cl/Cd: 77.16 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s810-nr-500000-n5.txt Download as CSV file: xf-s810-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S810 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4374 0.09619 0.09273 -0.0706 0.7351 0.0069
-12.500 -0.4505 0.09077 0.08726 -0.0735 0.7340 0.0067
-12.250 -0.4732 0.08450 0.08091 -0.0761 0.7330 0.0066
-12.000 -0.4875 0.08034 0.07668 -0.0775 0.7319 0.0063
-11.750 -0.5065 0.07593 0.07217 -0.0782 0.7308 0.0063
-11.500 -0.5270 0.07170 0.06785 -0.0783 0.7296 0.0060
-11.250 -0.5476 0.06773 0.06377 -0.0775 0.7283 0.0063
-11.000 -0.5626 0.06464 0.06058 -0.0765 0.7270 0.0059
-10.750 -0.5800 0.06141 0.05723 -0.0747 0.7257 0.0059
-10.500 -0.5947 0.05857 0.05426 -0.0725 0.7243 0.0058
-10.250 -0.6097 0.05560 0.05114 -0.0696 0.7230 0.0054
-10.000 -0.6208 0.05337 0.04879 -0.0664 0.7217 0.0058
-9.750 -0.6318 0.05100 0.04626 -0.0625 0.7205 0.0056
-9.500 -0.6345 0.04847 0.04355 -0.0596 0.7194 0.0056
-9.250 -0.6333 0.04590 0.04079 -0.0570 0.7183 0.0058
-9.000 -0.6281 0.04341 0.03810 -0.0547 0.7174 0.0060
-8.750 -0.6208 0.04068 0.03514 -0.0524 0.7164 0.0059
-8.500 -0.6089 0.03826 0.03250 -0.0506 0.7155 0.0061
-8.250 -0.5942 0.03574 0.02977 -0.0491 0.7147 0.0061
-8.000 -0.5745 0.03327 0.02709 -0.0479 0.7138 0.0066
-7.750 -0.5503 0.03106 0.02465 -0.0473 0.7130 0.0071
-7.500 -0.5248 0.02855 0.02193 -0.0470 0.7122 0.0070
-7.250 -0.4917 0.02615 0.01933 -0.0478 0.7114 0.0069
-7.000 -0.4233 0.02326 0.01621 -0.0534 0.7111 0.0068
-6.750 -0.3648 0.02202 0.01482 -0.0560 0.7107 0.0070
-6.500 -0.3332 0.02143 0.01414 -0.0558 0.7099 0.0072
-6.250 -0.3108 0.02093 0.01358 -0.0549 0.7091 0.0076
-6.000 -0.2963 0.02013 0.01273 -0.0530 0.7081 0.0080
-5.750 -0.2850 0.01932 0.01191 -0.0511 0.7070 0.0083
-5.500 -0.2720 0.01863 0.01119 -0.0497 0.7060 0.0087
-5.250 -0.2579 0.01799 0.01054 -0.0485 0.7052 0.0092
-5.000 -0.2451 0.01731 0.00981 -0.0471 0.7044 0.0097
-4.750 -0.2342 0.01655 0.00901 -0.0454 0.7036 0.0101
-4.500 -0.2224 0.01590 0.00832 -0.0437 0.7028 0.0110
-4.250 -0.2185 0.01522 0.00758 -0.0408 0.7019 0.0113
-4.000 -0.2084 0.01462 0.00693 -0.0387 0.7012 0.0116
-3.750 -0.1926 0.01413 0.00639 -0.0374 0.7004 0.0120
-3.500 -0.1767 0.01357 0.00578 -0.0361 0.6997 0.0133
-3.250 -0.1554 0.01323 0.00540 -0.0356 0.6989 0.0150
-3.000 -0.1322 0.01296 0.00510 -0.0354 0.6982 0.0178
-2.750 -0.1084 0.01270 0.00481 -0.0352 0.6974 0.0225
-2.500 -0.0838 0.01247 0.00457 -0.0352 0.6966 0.0320
-2.250 -0.0812 0.01025 0.00339 -0.0330 0.6954 0.3742
-2.000 -0.0645 0.00916 0.00314 -0.0322 0.6946 0.5903
-1.750 -0.0355 0.00930 0.00324 -0.0327 0.6939 0.6079
-1.500 -0.0064 0.00944 0.00339 -0.0332 0.6932 0.6162
-1.250 0.0228 0.00949 0.00338 -0.0339 0.6926 0.6202
-1.000 0.0519 0.00954 0.00340 -0.0345 0.6919 0.6233
-0.750 0.0810 0.00968 0.00356 -0.0350 0.6913 0.6289
-0.500 0.1102 0.00974 0.00359 -0.0357 0.6907 0.6318
-0.250 0.1394 0.00975 0.00356 -0.0363 0.6899 0.6329
0.000 0.1687 0.00976 0.00354 -0.0370 0.6892 0.6339
0.250 0.1980 0.00979 0.00354 -0.0378 0.6886 0.6350
0.500 0.2272 0.00982 0.00358 -0.0384 0.6880 0.6360
0.750 0.2562 0.00985 0.00363 -0.0391 0.6873 0.6370
1.000 0.2850 0.00988 0.00369 -0.0397 0.6864 0.6380
1.250 0.3137 0.00991 0.00376 -0.0403 0.6855 0.6389
1.500 0.3425 0.00994 0.00384 -0.0409 0.6844 0.6399
1.750 0.3712 0.00997 0.00391 -0.0415 0.6833 0.6409
2.000 0.4000 0.01001 0.00398 -0.0421 0.6820 0.6419
2.250 0.4288 0.01003 0.00406 -0.0427 0.6805 0.6430
2.500 0.4576 0.01005 0.00411 -0.0433 0.6789 0.6442
2.750 0.4867 0.01005 0.00413 -0.0439 0.6770 0.6455
3.000 0.5162 0.01001 0.00409 -0.0445 0.6745 0.6468
3.250 0.5439 0.00996 0.00411 -0.0449 0.6701 0.6479
3.500 0.5720 0.00983 0.00401 -0.0452 0.6638 0.6490
3.750 0.6003 0.00969 0.00390 -0.0455 0.6576 0.6499
4.000 0.6275 0.00958 0.00388 -0.0457 0.6500 0.6508
4.250 0.6551 0.00948 0.00387 -0.0459 0.6421 0.6518
4.500 0.6821 0.00938 0.00383 -0.0460 0.6302 0.6528
4.750 0.7087 0.00931 0.00383 -0.0460 0.6116 0.6539
5.000 0.7268 0.00942 0.00366 -0.0443 0.5391 0.6552
5.250 0.7310 0.01038 0.00416 -0.0404 0.4486 0.6565
5.500 0.7357 0.01130 0.00475 -0.0368 0.3765 0.6579
5.750 0.7418 0.01207 0.00530 -0.0334 0.3207 0.6592
6.000 0.7443 0.01279 0.00581 -0.0294 0.2715 0.6604
6.250 0.7447 0.01350 0.00634 -0.0251 0.2303 0.6616
6.500 0.7474 0.01436 0.00702 -0.0215 0.1902 0.6628
6.750 0.7535 0.01518 0.00771 -0.0187 0.1579 0.6639
7.000 0.7593 0.01609 0.00848 -0.0161 0.1246 0.6650
7.250 0.7670 0.01700 0.00927 -0.0138 0.0960 0.6663
7.500 0.7771 0.01785 0.01004 -0.0121 0.0750 0.6676
7.750 0.7901 0.01859 0.01077 -0.0107 0.0612 0.6690
8.000 0.8038 0.01933 0.01149 -0.0094 0.0505 0.6703
8.250 0.8188 0.02002 0.01218 -0.0084 0.0435 0.6716
8.500 0.8331 0.02076 0.01291 -0.0073 0.0359 0.6730
8.750 0.8472 0.02152 0.01366 -0.0063 0.0293 0.6743
9.000 0.8626 0.02223 0.01438 -0.0054 0.0254 0.6756
9.250 0.8778 0.02297 0.01513 -0.0045 0.0225 0.6768
9.500 0.8932 0.02368 0.01589 -0.0037 0.0184 0.6781
9.750 0.9069 0.02451 0.01676 -0.0027 0.0138 0.6793
10.000 0.9203 0.02538 0.01764 -0.0018 0.0096 0.6807
10.250 0.9313 0.02644 0.01871 -0.0005 0.0061 0.6821
10.500 0.9458 0.02728 0.01962 0.0003 0.0059 0.6837
10.750 0.9592 0.02821 0.02063 0.0012 0.0054 0.6853
11.000 0.9712 0.02927 0.02175 0.0022 0.0047 0.6869
11.250 0.9834 0.03034 0.02290 0.0031 0.0044 0.6884
11.500 0.9964 0.03136 0.02400 0.0039 0.0043 0.6900
11.750 1.0041 0.03284 0.02559 0.0052 0.0039 0.6913
12.000 1.0142 0.03412 0.02701 0.0061 0.0038 0.6927
12.250 1.0242 0.03543 0.02843 0.0070 0.0038 0.6941
12.500 1.0350 0.03672 0.02983 0.0077 0.0037 0.6957
12.750 1.0440 0.03817 0.03140 0.0085 0.0036 0.6972
13.000 1.0547 0.03951 0.03283 0.0091 0.0034 0.6990
13.250 1.0630 0.04110 0.03455 0.0098 0.0033 0.7007
13.500 1.0716 0.04269 0.03624 0.0103 0.0032 0.7025
13.750 1.0765 0.04469 0.03837 0.0111 0.0031 0.7044
14.000 1.0827 0.04660 0.04039 0.0116 0.0031 0.7062
14.250 1.0881 0.04863 0.04257 0.0121 0.0029 0.7080
14.500 1.0925 0.05082 0.04490 0.0125 0.0029 0.7099
14.750 1.0944 0.05334 0.04759 0.0128 0.0029 0.7118
15.000 1.0962 0.05596 0.05035 0.0130 0.0028 0.7138
15.250 1.0987 0.05857 0.05310 0.0130 0.0028 0.7158
15.500 1.0993 0.06151 0.05618 0.0128 0.0027 0.7177
15.750 1.0972 0.06488 0.05970 0.0125 0.0027 0.7195
16.000 1.0947 0.06841 0.06340 0.0119 0.0026 0.7214
16.250 1.0908 0.07230 0.06745 0.0111 0.0026 0.7232
16.500 1.0862 0.07643 0.07175 0.0099 0.0025 0.7253
16.750 1.0790 0.08115 0.07664 0.0084 0.0026 0.7272
17.000 1.0701 0.08633 0.08200 0.0065 0.0026 0.7292
17.250 1.0597 0.09202 0.08786 0.0041 0.0026 0.7311
17.500 1.0498 0.09789 0.09390 0.0013 0.0025 0.7329
17.750 1.0405 0.10385 0.10001 -0.0018 0.0025 0.7348
18.000 1.0254 0.11122 0.10756 -0.0058 0.0025 0.7363
18.250 1.0116 0.11862 0.11513 -0.0100 0.0025 0.7380
18.500 0.9935 0.12723 0.12393 -0.0149 0.0025 0.7394
18.750 0.9769 0.13592 0.13275 -0.0201 0.0024 0.7410
19.000 0.9539 0.14644 0.14346 -0.0262 0.0025 0.7420
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