NREL's S806A Airfoil (modified line 35) (s806a-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S806A Airfoil (modified line 35) (s806a-nr) Reynolds number: 1,000,000 Max Cl/Cd: 119.22 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s806a-nr-1000000.txt Download as CSV file: xf-s806a-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S806A 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
------ -------- --------- --------- -------- -------- --------
-6.000 -0.3669 0.04181 0.03845 -0.0487 0.7488 0.0099
-5.750 -0.3484 0.03838 0.03483 -0.0488 0.7482 0.0099
-5.500 -0.3277 0.03512 0.03137 -0.0489 0.7475 0.0099
-5.250 -0.3061 0.03212 0.02815 -0.0488 0.7467 0.0099
-5.000 -0.2828 0.02936 0.02516 -0.0488 0.7458 0.0099
-4.750 -0.2583 0.02684 0.02241 -0.0489 0.7447 0.0100
-4.500 -0.2327 0.02458 0.01992 -0.0489 0.7435 0.0100
-4.250 -0.2064 0.02255 0.01766 -0.0490 0.7420 0.0100
-4.000 -0.1790 0.02076 0.01565 -0.0492 0.7404 0.0100
-3.750 -0.1512 0.01917 0.01385 -0.0493 0.7384 0.0100
-3.500 -0.1243 0.01407 0.00819 -0.0493 0.7365 0.0120
-3.250 -0.0958 0.01343 0.00751 -0.0497 0.7344 0.0130
-3.000 -0.0671 0.01293 0.00696 -0.0501 0.7324 0.0144
-2.750 -0.0383 0.01253 0.00654 -0.0505 0.7306 0.0168
-1.500 0.1053 0.00934 0.00326 -0.0515 0.7221 0.0185
-1.250 0.1350 0.00891 0.00273 -0.0518 0.7198 0.0165
-1.000 0.1647 0.00868 0.00243 -0.0522 0.7172 0.0155
-0.750 0.1943 0.00800 0.00212 -0.0528 0.7144 0.1502
-0.500 0.2196 0.00603 0.00213 -0.0537 0.7115 0.7554
-0.250 0.2449 0.00605 0.00243 -0.0529 0.7082 0.8407
0.000 0.2739 0.00624 0.00261 -0.0532 0.7043 0.8508
0.250 0.3006 0.00640 0.00284 -0.0529 0.6999 0.8750
0.500 0.3282 0.00645 0.00290 -0.0528 0.6995 0.8886
0.750 0.3584 0.00644 0.00283 -0.0534 0.6990 0.8904
1.000 0.3887 0.00637 0.00276 -0.0541 0.6982 0.8897
1.250 0.4155 0.00641 0.00280 -0.0537 0.6966 0.8996
1.500 0.4443 0.00628 0.00265 -0.0539 0.6941 0.9035
1.750 0.4726 0.00618 0.00256 -0.0540 0.6911 0.9074
2.000 0.5013 0.00610 0.00248 -0.0543 0.6872 0.9106
2.250 0.5300 0.00603 0.00240 -0.0545 0.6820 0.9137
2.500 0.5589 0.00599 0.00235 -0.0548 0.6764 0.9168
2.750 0.5878 0.00598 0.00230 -0.0552 0.6696 0.9193
3.000 0.6167 0.00598 0.00226 -0.0556 0.6604 0.9224
3.250 0.6451 0.00601 0.00228 -0.0559 0.6497 0.9258
3.500 0.6737 0.00591 0.00221 -0.0561 0.6438 0.9292
3.750 0.7022 0.00589 0.00223 -0.0564 0.6384 0.9329
4.000 0.7279 0.00616 0.00211 -0.0561 0.5581 0.9370
4.250 0.7439 0.00866 0.00314 -0.0557 0.2450 0.9399
4.500 0.7667 0.00945 0.00354 -0.0555 0.1632 0.9450
4.750 0.7919 0.00977 0.00374 -0.0554 0.1345 0.9502
5.000 0.8157 0.01028 0.00405 -0.0551 0.1036 0.9567
5.250 0.8427 0.01045 0.00422 -0.0553 0.0990 0.9643
5.500 0.8699 0.01078 0.00448 -0.0557 0.0826 0.9762
5.750 0.8996 0.01104 0.00471 -0.0566 0.0729 1.0000
6.000 0.9263 0.01138 0.00499 -0.0569 0.0626 1.0000
6.250 0.9526 0.01172 0.00528 -0.0571 0.0532 1.0000
6.500 0.9784 0.01208 0.00559 -0.0573 0.0468 1.0000
6.750 1.0038 0.01245 0.00591 -0.0573 0.0408 1.0000
7.000 1.0292 0.01278 0.00623 -0.0573 0.0366 1.0000
7.250 1.0539 0.01316 0.00658 -0.0572 0.0325 1.0000
7.500 1.0725 0.01356 0.00709 -0.0557 0.0255 1.0000
7.750 1.0938 0.01406 0.00752 -0.0550 0.0178 1.0000
8.000 1.1148 0.01457 0.00799 -0.0542 0.0123 1.0000
8.250 1.1364 0.01500 0.00841 -0.0535 0.0093 1.0000
8.500 1.1579 0.01542 0.00884 -0.0529 0.0084 1.0000
8.750 1.1785 0.01587 0.00929 -0.0521 0.0075 1.0000
9.000 1.1984 0.01634 0.00975 -0.0512 0.0068 1.0000
9.250 1.2169 0.01684 0.01023 -0.0501 0.0059 1.0000
9.500 1.2347 0.01736 0.01076 -0.0488 0.0051 1.0000
9.750 1.2533 0.01786 0.01133 -0.0479 0.0054 1.0000
10.000 1.2672 0.01852 0.01202 -0.0461 0.0046 1.0000
10.250 1.2806 0.01928 0.01284 -0.0445 0.0041 1.0000
10.500 1.2918 0.02027 0.01393 -0.0426 0.0037 1.0000
10.750 1.3035 0.02130 0.01506 -0.0409 0.0035 1.0000
11.000 1.3140 0.02245 0.01632 -0.0392 0.0033 1.0000
11.250 1.3214 0.02383 0.01782 -0.0372 0.0032 1.0000
11.500 1.3290 0.02522 0.01933 -0.0352 0.0032 1.0000
11.750 1.3360 0.02671 0.02094 -0.0334 0.0032 1.0000
12.000 1.3399 0.02848 0.02284 -0.0314 0.0031 1.0000
12.250 1.3464 0.03009 0.02456 -0.0297 0.0031 1.0000
12.500 1.3440 0.03236 0.02702 -0.0269 0.0031 1.0000
12.750 1.3400 0.03485 0.02969 -0.0243 0.0030 1.0000
13.000 1.3356 0.03757 0.03260 -0.0220 0.0030 1.0000
13.250 1.3294 0.04059 0.03582 -0.0197 0.0029 1.0000
13.500 1.3229 0.04374 0.03917 -0.0176 0.0029 1.0000
13.750 1.3115 0.04734 0.04298 -0.0158 0.0029 1.0000
14.000 1.3005 0.05109 0.04694 -0.0143 0.0028 1.0000
14.250 1.2883 0.05518 0.05122 -0.0130 0.0028 1.0000
14.500 1.2747 0.05967 0.05589 -0.0127 0.0028 1.0000
14.750 1.2627 0.06419 0.06059 -0.0125 0.0028 1.0000
15.000 1.2470 0.06952 0.06608 -0.0132 0.0028 1.0000
15.250 1.2332 0.07470 0.07143 -0.0140 0.0029 1.0000
15.500 1.2180 0.08062 0.07749 -0.0158 0.0029 1.0000
15.750 1.2036 0.08690 0.08391 -0.0181 0.0029 1.0000
16.000 1.1894 0.09349 0.09064 -0.0210 0.0029 1.0000
16.250 1.1731 0.10096 0.09825 -0.0247 0.0029 1.0000
16.500 1.1557 0.10915 0.10657 -0.0290 0.0029 1.0000
16.750 1.1375 0.11797 0.11552 -0.0340 0.0030 1.0000
17.000 1.1190 0.12718 0.12486 -0.0392 0.0030 1.0000
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Polar data table (+)
Polar graphs
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