NREL's S805A Airfoil (s805a-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S805A Airfoil (s805a-nr) Reynolds number: 1,000,000 Max Cl/Cd: 103.27 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s805a-nr-1000000-n5.txt Download as CSV file: xf-s805a-nr-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7565 0.06869 0.06688 -0.0583 1.0000 0.0057
-14.000 -0.8383 0.04956 0.04733 -0.0719 1.0000 0.0055
-13.750 -0.8659 0.04392 0.04148 -0.0732 1.0000 0.0055
-13.500 -0.8906 0.03939 0.03672 -0.0727 1.0000 0.0056
-13.250 -0.9018 0.03656 0.03373 -0.0712 1.0000 0.0057
-13.000 -0.9158 0.03376 0.03073 -0.0689 1.0000 0.0058
-12.750 -0.9223 0.03184 0.02866 -0.0663 1.0000 0.0058
-12.500 -0.9331 0.02988 0.02652 -0.0626 1.0000 0.0059
-12.250 -0.9259 0.02825 0.02472 -0.0615 0.9980 0.0060
-12.000 -0.9113 0.02673 0.02304 -0.0614 0.9920 0.0061
-11.750 -0.8943 0.02510 0.02122 -0.0617 0.9870 0.0062
-11.500 -0.8678 0.02405 0.02005 -0.0631 0.9839 0.0063
-11.250 -0.8529 0.02229 0.01808 -0.0626 0.9770 0.0065
-11.000 -0.8257 0.02152 0.01725 -0.0636 0.9717 0.0067
-10.750 -0.8023 0.02091 0.01657 -0.0637 0.9627 0.0068
-10.500 -0.7776 0.02026 0.01584 -0.0640 0.9500 0.0070
-10.250 -0.7537 0.01958 0.01502 -0.0640 0.9190 0.0071
-10.000 -0.7373 0.01906 0.01420 -0.0622 0.8567 0.0073
-9.750 -0.7204 0.01859 0.01350 -0.0606 0.8185 0.0074
-9.500 -0.7019 0.01807 0.01279 -0.0593 0.7927 0.0076
-9.250 -0.6819 0.01756 0.01212 -0.0583 0.7731 0.0078
-9.000 -0.6618 0.01692 0.01133 -0.0573 0.7571 0.0080
-8.750 -0.6403 0.01644 0.01072 -0.0565 0.7434 0.0083
-8.500 -0.6188 0.01590 0.01004 -0.0557 0.7308 0.0085
-8.250 -0.5965 0.01544 0.00947 -0.0550 0.7195 0.0086
-8.000 -0.5729 0.01512 0.00905 -0.0545 0.7089 0.0088
-7.750 -0.5502 0.01462 0.00846 -0.0538 0.7001 0.0090
-7.500 -0.5291 0.01394 0.00768 -0.0530 0.6921 0.0094
-7.250 -0.5059 0.01350 0.00718 -0.0524 0.6851 0.0096
-7.000 -0.4821 0.01313 0.00675 -0.0519 0.6782 0.0099
-6.750 -0.4579 0.01279 0.00635 -0.0515 0.6723 0.0101
-6.500 -0.4336 0.01246 0.00596 -0.0510 0.6659 0.0104
-6.250 -0.4094 0.01211 0.00555 -0.0506 0.6601 0.0106
-6.000 -0.3846 0.01180 0.00520 -0.0502 0.6548 0.0110
-5.750 -0.3597 0.01150 0.00483 -0.0498 0.6497 0.0113
-5.500 -0.3343 0.01127 0.00455 -0.0496 0.6454 0.0117
-5.250 -0.3085 0.01103 0.00427 -0.0493 0.6413 0.0121
-5.000 -0.2827 0.01080 0.00401 -0.0491 0.6371 0.0122
-4.750 -0.2581 0.01044 0.00358 -0.0487 0.6330 0.0129
-4.500 -0.2322 0.01020 0.00331 -0.0485 0.6294 0.0135
-4.250 -0.2059 0.00999 0.00308 -0.0484 0.6255 0.0140
-4.000 -0.1793 0.00981 0.00288 -0.0483 0.6217 0.0146
-3.750 -0.1527 0.00966 0.00269 -0.0482 0.6182 0.0153
-3.500 -0.1259 0.00952 0.00251 -0.0481 0.6152 0.0161
-3.250 -0.0988 0.00936 0.00234 -0.0481 0.6123 0.0175
-3.000 -0.0718 0.00920 0.00219 -0.0481 0.6092 0.0203
-2.750 -0.0447 0.00906 0.00204 -0.0481 0.6060 0.0256
-2.500 -0.0184 0.00884 0.00191 -0.0480 0.6028 0.0501
-2.250 0.0082 0.00863 0.00180 -0.0479 0.6001 0.0791
-2.000 0.0345 0.00835 0.00168 -0.0479 0.5976 0.1304
-1.750 0.0595 0.00787 0.00153 -0.0478 0.5949 0.2306
-1.500 0.0832 0.00722 0.00136 -0.0476 0.5922 0.3774
-1.250 0.1057 0.00637 0.00116 -0.0472 0.5895 0.5724
-0.750 0.1589 0.00600 0.00123 -0.0470 0.5845 0.7236
-0.500 0.1874 0.00601 0.00126 -0.0471 0.5821 0.7382
-0.250 0.2159 0.00602 0.00128 -0.0473 0.5796 0.7455
0.000 0.2447 0.00605 0.00128 -0.0476 0.5770 0.7490
0.250 0.2735 0.00609 0.00128 -0.0479 0.5743 0.7523
0.500 0.3020 0.00612 0.00130 -0.0481 0.5719 0.7554
0.750 0.3308 0.00614 0.00132 -0.0484 0.5698 0.7583
1.000 0.3596 0.00616 0.00134 -0.0488 0.5672 0.7611
1.250 0.3884 0.00619 0.00137 -0.0491 0.5644 0.7642
1.500 0.4171 0.00623 0.00139 -0.0493 0.5609 0.7673
1.750 0.4452 0.00628 0.00143 -0.0495 0.5567 0.7703
2.000 0.4739 0.00630 0.00147 -0.0498 0.5519 0.7733
2.250 0.5022 0.00634 0.00151 -0.0500 0.5459 0.7764
2.500 0.5304 0.00639 0.00155 -0.0502 0.5395 0.7797
2.750 0.5588 0.00645 0.00159 -0.0504 0.5315 0.7825
3.000 0.5868 0.00650 0.00165 -0.0506 0.5242 0.7849
3.250 0.6146 0.00656 0.00170 -0.0507 0.5151 0.7872
3.500 0.6424 0.00663 0.00177 -0.0509 0.5050 0.7898
3.750 0.6699 0.00672 0.00185 -0.0510 0.4927 0.7927
4.000 0.6969 0.00685 0.00193 -0.0510 0.4745 0.7955
4.250 0.7237 0.00701 0.00203 -0.0509 0.4568 0.7979
4.500 0.7487 0.00725 0.00219 -0.0506 0.4258 0.8003
4.750 0.7701 0.00777 0.00247 -0.0497 0.3684 0.8030
5.250 0.8092 0.00908 0.00322 -0.0474 0.2451 0.8094
5.500 0.8310 0.00955 0.00353 -0.0466 0.2089 0.8123
5.750 0.8525 0.01000 0.00384 -0.0458 0.1748 0.8150
6.000 0.8745 0.01039 0.00414 -0.0450 0.1503 0.8177
6.250 0.8969 0.01075 0.00443 -0.0443 0.1303 0.8207
6.500 0.9187 0.01113 0.00474 -0.0435 0.1124 0.8239
6.750 0.9407 0.01150 0.00505 -0.0428 0.0969 0.8272
7.000 0.9621 0.01186 0.00537 -0.0419 0.0829 0.8302
7.250 0.9830 0.01222 0.00570 -0.0409 0.0713 0.8333
7.500 1.0031 0.01262 0.00606 -0.0398 0.0594 0.8367
7.750 1.0227 0.01303 0.00643 -0.0387 0.0493 0.8402
8.000 1.0424 0.01340 0.00679 -0.0375 0.0424 0.8434
8.250 1.0614 0.01376 0.00716 -0.0362 0.0370 0.8470
8.500 1.0787 0.01413 0.00753 -0.0346 0.0330 0.8512
8.750 1.0946 0.01449 0.00791 -0.0328 0.0297 0.8555
9.000 1.1102 0.01486 0.00832 -0.0309 0.0272 0.8595
9.250 1.1247 0.01529 0.00877 -0.0289 0.0246 0.8641
9.500 1.1402 0.01571 0.00923 -0.0271 0.0229 0.8691
9.750 1.1546 0.01617 0.00972 -0.0252 0.0205 0.8743
10.000 1.1678 0.01668 0.01026 -0.0232 0.0185 0.8806
10.500 1.1937 0.01777 0.01146 -0.0194 0.0145 0.8943
10.750 1.2038 0.01848 0.01219 -0.0172 0.0112 0.9030
11.000 1.2133 0.01920 0.01297 -0.0150 0.0093 0.9150
11.250 1.2209 0.01995 0.01381 -0.0126 0.0077 0.9353
11.750 1.2466 0.02187 0.01586 -0.0107 0.0054 1.0000
12.000 1.2581 0.02285 0.01689 -0.0095 0.0052 1.0000
12.250 1.2682 0.02396 0.01806 -0.0083 0.0048 1.0000
12.500 1.2794 0.02505 0.01920 -0.0073 0.0047 1.0000
12.750 1.2893 0.02626 0.02048 -0.0062 0.0044 1.0000
13.000 1.2993 0.02751 0.02178 -0.0053 0.0043 1.0000
13.250 1.3084 0.02885 0.02319 -0.0045 0.0041 1.0000
13.500 1.3166 0.03031 0.02470 -0.0036 0.0039 1.0000
13.750 1.3241 0.03186 0.02631 -0.0028 0.0037 1.0000
14.000 1.3305 0.03354 0.02807 -0.0021 0.0035 1.0000
14.250 1.3366 0.03529 0.02989 -0.0014 0.0034 1.0000
14.500 1.3403 0.03730 0.03199 -0.0008 0.0032 1.0000
14.750 1.3453 0.03925 0.03402 -0.0003 0.0032 1.0000
15.000 1.3497 0.04130 0.03615 0.0001 0.0031 1.0000
15.250 1.3552 0.04328 0.03820 0.0004 0.0031 1.0000
15.500 1.3594 0.04545 0.04046 0.0006 0.0030 1.0000
15.750 1.3620 0.04786 0.04296 0.0007 0.0030 1.0000
16.000 1.3649 0.05028 0.04547 0.0006 0.0030 1.0000
16.250 1.3682 0.05273 0.04801 0.0005 0.0029 1.0000
16.500 1.3679 0.05570 0.05108 0.0002 0.0028 1.0000
16.750 1.3691 0.05855 0.05403 -0.0002 0.0028 1.0000
17.000 1.3685 0.06171 0.05729 -0.0008 0.0027 1.0000
17.250 1.3672 0.06507 0.06074 -0.0016 0.0027 1.0000
17.500 1.3656 0.06856 0.06434 -0.0025 0.0026 1.0000
17.750 1.3618 0.07247 0.06835 -0.0036 0.0026 1.0000
18.000 1.3550 0.07695 0.07295 -0.0051 0.0026 1.0000
18.250 1.3500 0.08129 0.07740 -0.0067 0.0025 1.0000
18.500 1.3434 0.08607 0.08230 -0.0086 0.0025 1.0000
18.750 1.3329 0.09159 0.08795 -0.0110 0.0025 1.0000
19.000 1.3245 0.09694 0.09341 -0.0135 0.0025 1.0000
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