NREL's S805A Airfoil (s805a-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S805A Airfoil (s805a-nr) Reynolds number: 1,000,000 Max Cl/Cd: 117.37 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s805a-nr-1000000.txt Download as CSV file: xf-s805a-nr-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6937 0.04022 0.03775 -0.0597 0.9974 0.0090
-10.000 -0.7120 0.03258 0.02951 -0.0598 0.9891 0.0091
-9.750 -0.6946 0.02957 0.02626 -0.0613 0.9854 0.0094
-9.500 -0.6599 0.02956 0.02630 -0.0640 0.9835 0.0097
-9.250 -0.6262 0.03111 0.02803 -0.0654 0.9778 0.0101
-9.000 -0.6037 0.02887 0.02557 -0.0666 0.9715 0.0106
-8.750 -0.5929 0.02542 0.02172 -0.0651 0.9580 0.0111
-8.500 -0.5799 0.02280 0.01873 -0.0633 0.9357 0.0113
-8.250 -0.5620 0.02113 0.01669 -0.0619 0.8932 0.0116
-8.000 -0.5453 0.02006 0.01526 -0.0600 0.8465 0.0118
-7.750 -0.5261 0.01938 0.01428 -0.0586 0.8156 0.0121
-7.500 -0.5064 0.01844 0.01305 -0.0574 0.7932 0.0124
-7.250 -0.4870 0.01600 0.01035 -0.0563 0.7757 0.0128
-7.000 -0.4644 0.01536 0.00962 -0.0557 0.7603 0.0133
-6.750 -0.4408 0.01499 0.00916 -0.0552 0.7468 0.0139
-6.500 -0.4170 0.01449 0.00857 -0.0546 0.7348 0.0145
-6.250 -0.3931 0.01384 0.00782 -0.0540 0.7240 0.0148
-6.000 -0.3691 0.01331 0.00720 -0.0535 0.7148 0.0152
-5.500 -0.3210 0.01233 0.00606 -0.0524 0.6990 0.0158
-5.250 -0.2970 0.01191 0.00557 -0.0518 0.6921 0.0161
-5.000 -0.2715 0.01164 0.00525 -0.0515 0.6859 0.0164
-4.750 -0.2509 0.01081 0.00432 -0.0504 0.6799 0.0175
-4.500 -0.2266 0.01043 0.00388 -0.0499 0.6745 0.0182
-4.250 -0.2011 0.01014 0.00356 -0.0496 0.6692 0.0190
-4.000 -0.1753 0.00990 0.00327 -0.0493 0.6643 0.0198
-3.750 -0.1493 0.00969 0.00300 -0.0491 0.6599 0.0206
-3.500 -0.1226 0.00949 0.00278 -0.0490 0.6558 0.0215
-3.250 -0.0962 0.00927 0.00250 -0.0488 0.6517 0.0234
-3.000 -0.0699 0.00908 0.00230 -0.0486 0.6476 0.0282
-2.750 -0.0455 0.00859 0.00207 -0.0483 0.6440 0.0940
-2.500 -0.0224 0.00792 0.00185 -0.0479 0.6403 0.2210
-2.250 -0.0014 0.00698 0.00159 -0.0474 0.6369 0.4199
-2.000 0.0205 0.00615 0.00140 -0.0468 0.6336 0.6067
-1.750 0.0469 0.00598 0.00141 -0.0467 0.6303 0.6798
-1.500 0.0751 0.00595 0.00142 -0.0468 0.6274 0.7089
-1.250 0.1032 0.00594 0.00146 -0.0468 0.6242 0.7295
-1.000 0.1313 0.00600 0.00152 -0.0468 0.6211 0.7499
-0.750 0.1591 0.00612 0.00162 -0.0468 0.6182 0.7679
-0.500 0.1871 0.00619 0.00170 -0.0468 0.6154 0.7771
-0.250 0.2161 0.00624 0.00173 -0.0471 0.6128 0.7830
0.000 0.2447 0.00623 0.00172 -0.0473 0.6099 0.7859
0.250 0.2734 0.00626 0.00174 -0.0476 0.6072 0.7887
0.500 0.3021 0.00631 0.00176 -0.0478 0.6045 0.7917
0.750 0.3308 0.00639 0.00180 -0.0481 0.6014 0.7948
1.000 0.3598 0.00641 0.00181 -0.0485 0.5990 0.7974
1.250 0.3885 0.00641 0.00183 -0.0488 0.5962 0.8001
1.500 0.4170 0.00642 0.00186 -0.0490 0.5929 0.8028
1.750 0.4454 0.00648 0.00189 -0.0492 0.5890 0.8057
2.000 0.4738 0.00653 0.00195 -0.0495 0.5849 0.8088
2.250 0.5025 0.00655 0.00197 -0.0497 0.5804 0.8118
2.500 0.5307 0.00656 0.00198 -0.0499 0.5753 0.8146
2.750 0.5586 0.00661 0.00203 -0.0501 0.5700 0.8172
3.000 0.5870 0.00661 0.00207 -0.0503 0.5648 0.8198
3.250 0.6150 0.00666 0.00212 -0.0504 0.5592 0.8225
3.500 0.6432 0.00670 0.00217 -0.0506 0.5537 0.8252
3.750 0.6716 0.00674 0.00222 -0.0509 0.5472 0.8277
4.000 0.6991 0.00678 0.00227 -0.0510 0.5405 0.8304
4.250 0.7271 0.00680 0.00234 -0.0511 0.5345 0.8330
4.500 0.7544 0.00688 0.00242 -0.0512 0.5272 0.8357
4.750 0.7822 0.00692 0.00249 -0.0513 0.5165 0.8385
5.000 0.8090 0.00703 0.00256 -0.0513 0.4999 0.8413
5.250 0.8356 0.00714 0.00266 -0.0512 0.4819 0.8440
5.500 0.8603 0.00733 0.00279 -0.0508 0.4529 0.8470
5.750 0.8813 0.00781 0.00305 -0.0498 0.3976 0.8502
6.000 0.9000 0.00847 0.00343 -0.0485 0.3352 0.8536
6.250 0.9188 0.00914 0.00384 -0.0472 0.2800 0.8570
6.500 0.9374 0.00972 0.00424 -0.0459 0.2326 0.8603
6.750 0.9556 0.01031 0.00464 -0.0445 0.1909 0.8639
7.000 0.9744 0.01086 0.00504 -0.0432 0.1572 0.8678
7.250 0.9935 0.01137 0.00542 -0.0419 0.1298 0.8717
7.500 1.0115 0.01186 0.00582 -0.0405 0.1058 0.8756
7.750 1.0292 0.01235 0.00623 -0.0390 0.0870 0.8797
8.000 1.0473 0.01280 0.00662 -0.0376 0.0718 0.8841
8.250 1.0649 0.01325 0.00703 -0.0361 0.0599 0.8885
8.500 1.0808 0.01368 0.00744 -0.0342 0.0507 0.8936
8.750 1.0960 0.01404 0.00783 -0.0322 0.0448 0.8994
9.000 1.1081 0.01448 0.00828 -0.0296 0.0392 0.9058
9.250 1.1233 0.01483 0.00868 -0.0277 0.0368 0.9127
9.500 1.1354 0.01528 0.00915 -0.0252 0.0338 0.9210
9.750 1.1464 0.01575 0.00968 -0.0226 0.0305 0.9322
10.000 1.1586 0.01607 0.01010 -0.0202 0.0292 0.9503
10.250 1.1796 0.01659 0.01067 -0.0200 0.0262 1.0000
10.500 1.1931 0.01731 0.01140 -0.0185 0.0236 1.0000
10.750 1.2104 0.01781 0.01193 -0.0175 0.0215 1.0000
11.000 1.2225 0.01859 0.01269 -0.0159 0.0184 1.0000
11.250 1.2350 0.01938 0.01349 -0.0145 0.0152 1.0000
11.500 1.2428 0.02048 0.01457 -0.0126 0.0112 1.0000
11.750 1.2507 0.02164 0.01576 -0.0109 0.0091 1.0000
12.000 1.2609 0.02270 0.01687 -0.0095 0.0086 1.0000
12.250 1.2663 0.02415 0.01837 -0.0079 0.0075 1.0000
12.500 1.2743 0.02548 0.01977 -0.0066 0.0072 1.0000
12.750 1.2838 0.02675 0.02111 -0.0056 0.0069 1.0000
13.000 1.2932 0.02805 0.02247 -0.0047 0.0066 1.0000
13.250 1.3013 0.02950 0.02399 -0.0038 0.0063 1.0000
13.500 1.3079 0.03111 0.02568 -0.0029 0.0061 1.0000
13.750 1.3140 0.03282 0.02744 -0.0021 0.0058 1.0000
14.000 1.3178 0.03476 0.02946 -0.0012 0.0055 1.0000
14.250 1.3204 0.03687 0.03167 -0.0005 0.0054 1.0000
14.500 1.3185 0.03948 0.03439 0.0002 0.0051 1.0000
14.750 1.3185 0.04197 0.03698 0.0008 0.0051 1.0000
15.000 1.3104 0.04541 0.04056 0.0013 0.0049 1.0000
15.250 1.3145 0.04767 0.04291 0.0013 0.0049 1.0000
15.500 1.3171 0.05015 0.04548 0.0013 0.0048 1.0000
15.750 1.3155 0.05319 0.04862 0.0012 0.0048 1.0000
16.000 1.3165 0.05603 0.05155 0.0009 0.0048 1.0000
16.250 1.3171 0.05901 0.05463 0.0004 0.0046 1.0000
16.500 1.3124 0.06274 0.05848 -0.0002 0.0046 1.0000
16.750 1.3113 0.06614 0.06199 -0.0010 0.0045 1.0000
17.000 1.3067 0.07016 0.06612 -0.0021 0.0045 1.0000
17.250 1.3032 0.07410 0.07017 -0.0033 0.0044 1.0000
17.500 1.2969 0.07863 0.07482 -0.0049 0.0043 1.0000
17.750 1.2901 0.08338 0.07970 -0.0067 0.0043 1.0000
18.000 1.2789 0.08900 0.08546 -0.0090 0.0043 1.0000
18.250 1.2703 0.09438 0.09096 -0.0114 0.0043 1.0000
18.500 1.2608 0.10011 0.09682 -0.0141 0.0043 1.0000
18.750 1.2491 0.10642 0.10326 -0.0172 0.0042 1.0000
19.000 1.2386 0.11265 0.10961 -0.0205 0.0042 1.0000
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