NREL's S809 Airfoil (s809-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S809 Airfoil (s809-nr) Reynolds number: 500,000 Max Cl/Cd: 81.2 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s809-nr-500000.txt Download as CSV file: xf-s809-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S809 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.3992 0.16006 0.15751 -0.0156 0.7720 0.0155
-17.750 -0.4079 0.15215 0.14959 -0.0203 0.7665 0.0161
-11.500 -0.6189 0.04377 0.03655 -0.0617 0.6633 0.0097
-11.250 -0.5860 0.04451 0.03728 -0.0603 0.6604 0.0101
-11.000 -0.5621 0.04466 0.03741 -0.0591 0.6580 0.0102
-10.750 -0.5447 0.04405 0.03677 -0.0587 0.6559 0.0105
-10.500 -0.5268 0.04369 0.03639 -0.0577 0.6537 0.0106
-10.250 -0.5115 0.04291 0.03560 -0.0573 0.6518 0.0112
-10.000 -0.4961 0.04213 0.03478 -0.0569 0.6500 0.0117
-9.750 -0.4845 0.04130 0.03392 -0.0557 0.6483 0.0118
-9.500 -0.4724 0.04032 0.03288 -0.0551 0.6467 0.0122
-9.250 -0.4626 0.03919 0.03171 -0.0543 0.6452 0.0121
-9.000 -0.4523 0.03806 0.03053 -0.0537 0.6436 0.0124
-8.750 -0.4464 0.03661 0.02905 -0.0528 0.6425 0.0124
-8.500 -0.4437 0.03492 0.02734 -0.0517 0.6413 0.0129
-8.250 -0.4412 0.03328 0.02568 -0.0506 0.6400 0.0134
-8.000 -0.4363 0.03183 0.02422 -0.0495 0.6387 0.0149
-7.750 -0.4298 0.03055 0.02290 -0.0485 0.6376 0.0150
-7.500 -0.4241 0.02926 0.02156 -0.0474 0.6365 0.0160
-7.250 -0.4247 0.02760 0.01988 -0.0458 0.6354 0.0184
-7.000 -0.4257 0.02592 0.01819 -0.0441 0.6344 0.0240
-6.750 -0.4352 0.02378 0.01612 -0.0417 0.6334 0.0433
-6.500 -0.4597 0.02075 0.01327 -0.0383 0.6325 0.0911
-6.250 -0.4872 0.01788 0.01051 -0.0341 0.6316 0.1316
-6.000 -0.5147 0.01444 0.00733 -0.0314 0.6307 0.2250
-5.750 -0.5255 0.01121 0.00508 -0.0294 0.6298 0.4604
-5.500 -0.4954 0.01172 0.00554 -0.0300 0.6288 0.4870
-5.000 -0.4319 0.01373 0.00765 -0.0307 0.6271 0.5106
-4.750 -0.4013 0.01452 0.00838 -0.0311 0.6265 0.5184
-4.500 -0.3701 0.01496 0.00890 -0.0315 0.6258 0.5212
-4.250 -0.3414 0.01485 0.00874 -0.0321 0.6251 0.5221
-4.000 -0.3126 0.01475 0.00859 -0.0327 0.6244 0.5230
-3.750 -0.2838 0.01465 0.00844 -0.0333 0.6237 0.5239
-3.500 -0.2550 0.01455 0.00830 -0.0340 0.6231 0.5250
-3.250 -0.2262 0.01445 0.00815 -0.0346 0.6222 0.5261
-3.000 -0.1974 0.01435 0.00800 -0.0353 0.6213 0.5272
-2.750 -0.1685 0.01426 0.00787 -0.0359 0.6205 0.5285
-2.500 -0.1395 0.01419 0.00775 -0.0366 0.6198 0.5299
-2.250 -0.1105 0.01414 0.00764 -0.0373 0.6192 0.5311
-2.000 -0.0814 0.01409 0.00754 -0.0380 0.6185 0.5321
-1.750 -0.0524 0.01399 0.00739 -0.0387 0.6179 0.5331
-1.500 -0.0235 0.01383 0.00724 -0.0394 0.6173 0.5341
-1.250 0.0056 0.01377 0.00719 -0.0400 0.6168 0.5350
-1.000 0.0348 0.01376 0.00718 -0.0407 0.6162 0.5359
-0.750 0.0641 0.01376 0.00719 -0.0413 0.6157 0.5368
-0.500 0.0934 0.01378 0.00721 -0.0420 0.6151 0.5377
-0.250 0.1226 0.01381 0.00724 -0.0426 0.6145 0.5387
0.000 0.1519 0.01386 0.00729 -0.0433 0.6137 0.5398
0.250 0.1812 0.01394 0.00738 -0.0439 0.6130 0.5410
0.500 0.2103 0.01404 0.00749 -0.0446 0.6125 0.5423
0.750 0.2394 0.01415 0.00761 -0.0453 0.6119 0.5435
1.000 0.2685 0.01415 0.00764 -0.0459 0.6113 0.5446
1.250 0.2975 0.01414 0.00765 -0.0466 0.6103 0.5457
1.500 0.3265 0.01415 0.00769 -0.0472 0.6092 0.5467
1.750 0.3555 0.01420 0.00776 -0.0478 0.6081 0.5476
2.000 0.3844 0.01419 0.00778 -0.0485 0.6071 0.5485
2.250 0.4131 0.01415 0.00781 -0.0490 0.6059 0.5497
2.500 0.4418 0.01418 0.00791 -0.0496 0.6048 0.5508
2.750 0.4706 0.01423 0.00803 -0.0501 0.6035 0.5519
3.000 0.4996 0.01426 0.00812 -0.0506 0.6019 0.5530
3.250 0.5289 0.01426 0.00815 -0.0511 0.5999 0.5541
3.500 0.5584 0.01429 0.00819 -0.0517 0.5978 0.5552
3.750 0.5871 0.01439 0.00833 -0.0522 0.5951 0.5563
4.000 0.6152 0.01425 0.00827 -0.0525 0.5914 0.5575
4.250 0.6442 0.01407 0.00813 -0.0529 0.5870 0.5586
4.500 0.6745 0.01386 0.00790 -0.0534 0.5827 0.5598
4.750 0.7033 0.01378 0.00784 -0.0538 0.5781 0.5611
5.000 0.7310 0.01353 0.00766 -0.0539 0.5719 0.5623
5.250 0.7610 0.01332 0.00744 -0.0544 0.5671 0.5633
5.500 0.7893 0.01315 0.00732 -0.0547 0.5626 0.5645
5.750 0.8160 0.01285 0.00716 -0.0546 0.5560 0.5657
6.000 0.8446 0.01254 0.00685 -0.0548 0.5486 0.5668
6.250 0.8703 0.01229 0.00676 -0.0545 0.5398 0.5679
6.500 0.8970 0.01207 0.00662 -0.0544 0.5305 0.5690
6.750 0.9232 0.01187 0.00654 -0.0541 0.5162 0.5702
7.000 0.9468 0.01166 0.00632 -0.0534 0.4731 0.5715
7.250 0.9485 0.01260 0.00670 -0.0492 0.3779 0.5727
7.500 0.9493 0.01382 0.00754 -0.0451 0.3042 0.5739
7.750 0.9494 0.01493 0.00835 -0.0411 0.2451 0.5751
8.000 0.9473 0.01583 0.00904 -0.0366 0.2033 0.5763
8.250 0.9442 0.01675 0.00980 -0.0320 0.1690 0.5772
8.500 0.9435 0.01782 0.01072 -0.0283 0.1400 0.5781
8.750 0.9435 0.01897 0.01176 -0.0251 0.1163 0.5788
9.000 0.9437 0.02018 0.01290 -0.0223 0.0961 0.5801
9.250 0.9448 0.02155 0.01422 -0.0201 0.0805 0.5812
9.500 0.9477 0.02302 0.01566 -0.0184 0.0669 0.5823
9.750 0.9512 0.02458 0.01721 -0.0169 0.0563 0.5835
10.000 0.9567 0.02611 0.01873 -0.0158 0.0481 0.5846
10.250 0.9638 0.02757 0.02022 -0.0148 0.0423 0.5859
10.500 0.9668 0.02935 0.02200 -0.0136 0.0374 0.5871
10.750 0.9770 0.03062 0.02334 -0.0129 0.0343 0.5884
11.000 0.9827 0.03225 0.02496 -0.0120 0.0310 0.5899
11.250 0.9887 0.03388 0.02664 -0.0112 0.0286 0.5913
11.500 0.9974 0.03533 0.02815 -0.0105 0.0269 0.5926
11.750 1.0044 0.03694 0.02977 -0.0099 0.0250 0.5939
12.000 1.0031 0.03921 0.03208 -0.0088 0.0234 0.5951
12.250 1.0132 0.04059 0.03358 -0.0084 0.0226 0.5966
12.500 1.0220 0.04212 0.03520 -0.0080 0.0215 0.5980
12.750 1.0304 0.04374 0.03688 -0.0076 0.0205 0.5995
13.000 1.0371 0.04554 0.03873 -0.0072 0.0196 0.6009
13.250 1.0364 0.04803 0.04126 -0.0066 0.0185 0.6024
13.500 1.0452 0.04976 0.04308 -0.0064 0.0180 0.6039
13.750 1.0549 0.05145 0.04485 -0.0063 0.0173 0.6057
14.000 1.0626 0.05334 0.04683 -0.0062 0.0167 0.6073
14.250 1.0713 0.05522 0.04876 -0.0062 0.0160 0.6089
14.500 1.0799 0.05712 0.05070 -0.0065 0.0151 0.6107
14.750 1.0838 0.05949 0.05315 -0.0065 0.0147 0.6124
15.000 1.0866 0.06199 0.05576 -0.0063 0.0141 0.6142
15.250 1.0952 0.06406 0.05795 -0.0067 0.0136 0.6163
15.500 1.1021 0.06635 0.06036 -0.0071 0.0131 0.6185
15.750 1.1082 0.06877 0.06286 -0.0076 0.0126 0.6209
16.000 1.1149 0.07120 0.06535 -0.0084 0.0120 0.6232
16.250 1.1188 0.07394 0.06815 -0.0091 0.0116 0.6254
16.500 1.1171 0.07737 0.07165 -0.0098 0.0109 0.6275
16.750 1.1216 0.08027 0.07470 -0.0107 0.0106 0.6300
17.000 1.1255 0.08335 0.07794 -0.0119 0.0102 0.6326
17.250 1.1276 0.08669 0.08141 -0.0131 0.0098 0.6352
17.500 1.1296 0.09009 0.08491 -0.0145 0.0094 0.6381
17.750 1.1308 0.09372 0.08862 -0.0161 0.0091 0.6408
18.000 1.1307 0.09757 0.09259 -0.0178 0.0088 0.6437
18.250 1.1292 0.10166 0.09679 -0.0196 0.0086 0.6466
18.500 1.1243 0.10630 0.10154 -0.0216 0.0084 0.6497
18.750 1.1179 0.11131 0.10668 -0.0239 0.0081 0.6526
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