NREL's S805A Airfoil (s805a-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S805A Airfoil (s805a-nr) Reynolds number: 100,000 Max Cl/Cd: 50.93 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s805a-nr-100000.txt Download as CSV file: xf-s805a-nr-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4098 0.09674 0.09197 -0.0428 1.0000 0.1226
-9.500 -0.4320 0.09259 0.08795 -0.0468 1.0000 0.1278
-9.250 -0.4763 0.08788 0.08337 -0.0521 1.0000 0.1288
-9.000 -0.4327 0.08538 0.08087 -0.0461 1.0000 0.1353
-8.750 -0.4503 0.08148 0.07707 -0.0477 1.0000 0.1398
-8.500 -0.4860 0.07822 0.07392 -0.0478 1.0000 0.1413
-8.250 -0.5246 0.07633 0.07211 -0.0444 1.0000 0.1422
-8.000 -0.5643 0.07522 0.07104 -0.0399 1.0000 0.1430
-7.750 -0.6006 0.07495 0.07081 -0.0340 1.0000 0.1433
-6.000 -0.4659 0.03891 0.03180 -0.0493 0.9432 0.0823
-5.750 -0.4388 0.03564 0.02767 -0.0483 0.9329 0.0714
-5.500 -0.3985 0.03213 0.02379 -0.0508 0.9290 0.0689
-5.250 -0.3697 0.02998 0.02130 -0.0508 0.9196 0.0679
-5.000 -0.3256 0.02804 0.01898 -0.0534 0.9156 0.0704
-4.750 -0.2944 0.02688 0.01751 -0.0538 0.9075 0.0725
-4.500 -0.2534 0.02463 0.01536 -0.0560 0.9034 0.0755
-4.250 -0.2115 0.02314 0.01392 -0.0584 0.9001 0.0814
-4.000 -0.1908 0.02229 0.01310 -0.0571 0.8904 0.0894
-3.750 -0.1582 0.02102 0.01194 -0.0580 0.8860 0.1105
-3.500 -0.1535 0.01925 0.01110 -0.0545 0.8760 0.2387
-3.250 -0.1551 0.01898 0.01303 -0.0445 0.8711 0.7620
-3.000 -0.1418 0.02056 0.01450 -0.0385 0.8629 0.8106
-2.750 0.0914 0.02356 0.01681 -0.0642 0.8804 0.9085
-2.500 0.1381 0.02311 0.01613 -0.0682 0.8746 0.9210
-2.250 0.1804 0.02268 0.01553 -0.0714 0.8691 0.9324
-2.000 0.2162 0.02240 0.01510 -0.0738 0.8618 0.9420
-1.750 0.2576 0.02190 0.01445 -0.0771 0.8568 0.9489
-1.500 0.2842 0.02182 0.01429 -0.0779 0.8490 0.9564
-1.250 0.3221 0.02142 0.01377 -0.0807 0.8433 0.9623
-1.000 0.3523 0.02130 0.01358 -0.0821 0.8373 0.9686
-0.750 0.3839 0.02114 0.01337 -0.0839 0.8312 0.9742
-0.500 0.4207 0.02084 0.01299 -0.0864 0.8265 0.9799
-0.250 0.4552 0.02075 0.01288 -0.0890 0.8202 0.9871
0.000 0.4920 0.02059 0.01269 -0.0918 0.8151 0.9938
0.250 0.5293 0.02031 0.01237 -0.0944 0.8110 0.9985
0.500 0.5490 0.02066 0.01276 -0.0943 0.8041 1.0000
0.750 0.5684 0.02088 0.01298 -0.0935 0.7989 1.0000
1.000 0.5866 0.02120 0.01331 -0.0926 0.7937 1.0000
1.250 0.6012 0.02169 0.01385 -0.0914 0.7873 1.0000
1.500 0.6216 0.02190 0.01406 -0.0906 0.7826 1.0000
1.750 0.6341 0.02252 0.01474 -0.0890 0.7762 1.0000
2.000 0.6499 0.02295 0.01523 -0.0876 0.7703 1.0000
2.250 0.6726 0.02305 0.01534 -0.0869 0.7661 1.0000
2.500 0.6762 0.02405 0.01644 -0.0842 0.7576 1.0000
2.750 0.6976 0.02419 0.01661 -0.0832 0.7526 1.0000
3.000 0.7021 0.02510 0.01760 -0.0803 0.7446 1.0000
3.250 0.7209 0.02530 0.01787 -0.0790 0.7385 1.0000
3.500 0.7270 0.02606 0.01871 -0.0761 0.7304 1.0000
3.750 0.7460 0.02617 0.01887 -0.0746 0.7235 1.0000
4.000 0.7497 0.02693 0.01970 -0.0712 0.7144 1.0000
4.250 0.7786 0.02649 0.01932 -0.0706 0.7075 1.0000
4.500 0.7780 0.02727 0.02021 -0.0664 0.6967 1.0000
4.750 0.8098 0.02659 0.01959 -0.0660 0.6888 1.0000
5.000 0.8252 0.02652 0.01959 -0.0635 0.6784 1.0000
5.250 0.8318 0.02678 0.01994 -0.0599 0.6671 1.0000
5.500 0.8580 0.02614 0.01940 -0.0585 0.6569 1.0000
5.750 0.8943 0.02500 0.01832 -0.0583 0.6467 1.0000
6.000 0.9041 0.02492 0.01833 -0.0548 0.6340 1.0000
6.250 0.9187 0.02456 0.01808 -0.0519 0.6212 1.0000
6.500 0.9369 0.02399 0.01762 -0.0493 0.6081 1.0000
6.750 0.9559 0.02328 0.01700 -0.0467 0.5937 1.0000
7.000 0.9740 0.02247 0.01628 -0.0439 0.5775 1.0000
7.250 0.9936 0.02149 0.01534 -0.0412 0.5587 1.0000
7.500 0.9995 0.02099 0.01495 -0.0366 0.5382 1.0000
7.750 1.0093 0.02040 0.01444 -0.0327 0.5119 1.0000
8.000 1.0148 0.02012 0.01424 -0.0284 0.4732 1.0000
8.250 1.0196 0.02002 0.01390 -0.0240 0.4064 1.0000
8.500 1.0123 0.02100 0.01420 -0.0183 0.3266 1.0000
8.750 0.9995 0.02256 0.01526 -0.0126 0.2700 1.0000
9.000 0.9903 0.02436 0.01665 -0.0081 0.2265 1.0000
9.250 0.9867 0.02622 0.01815 -0.0047 0.1934 1.0000
9.500 0.9887 0.02800 0.01966 -0.0021 0.1675 1.0000
9.750 0.9966 0.02963 0.02119 -0.0002 0.1463 1.0000
10.000 1.0103 0.03120 0.02263 0.0011 0.1304 1.0000
10.250 1.0281 0.03276 0.02412 0.0020 0.1173 1.0000
10.500 1.0507 0.03439 0.02572 0.0025 0.1063 1.0000
10.750 1.0788 0.03623 0.02749 0.0022 0.0962 1.0000
11.000 1.0960 0.03783 0.02920 0.0030 0.0884 1.0000
11.250 1.1159 0.03994 0.03148 0.0035 0.0804 1.0000
11.500 1.1377 0.04228 0.03375 0.0034 0.0720 1.0000
11.750 1.1374 0.04392 0.03574 0.0058 0.0669 1.0000
12.000 1.1576 0.04678 0.03854 0.0057 0.0601 1.0000
12.250 1.1528 0.04896 0.04113 0.0083 0.0570 1.0000
12.500 1.1585 0.05175 0.04419 0.0097 0.0539 1.0000
12.750 1.1712 0.05486 0.04732 0.0100 0.0503 1.0000
13.000 1.1651 0.05895 0.05172 0.0116 0.0490 1.0000
13.250 1.1500 0.06215 0.05529 0.0134 0.0483 1.0000
13.500 1.1329 0.06582 0.05930 0.0145 0.0476 1.0000
13.750 1.1151 0.06997 0.06376 0.0150 0.0471 1.0000
14.000 1.0956 0.07466 0.06873 0.0149 0.0469 1.0000
14.250 1.0745 0.07977 0.07410 0.0141 0.0468 1.0000
14.500 1.0508 0.08548 0.08006 0.0125 0.0467 1.0000
14.750 1.0274 0.09187 0.08665 0.0103 0.0474 1.0000
15.000 1.0022 0.09878 0.09375 0.0072 0.0478 1.0000
15.250 0.9790 0.10624 0.10135 0.0035 0.0485 1.0000
15.500 0.9565 0.11424 0.10947 -0.0007 0.0490 1.0000
15.750 0.9364 0.12280 0.11809 -0.0053 0.0495 1.0000
16.000 0.8245 0.16501 0.16029 -0.0311 0.0742 1.0000
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Polar data table (+)
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