NREL's S829 Airfoil (s829-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S829 Airfoil (s829-nr) Reynolds number: 100,000 Max Cl/Cd: 25.34 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s829-nr-100000-n5.txt Download as CSV file: xf-s829-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S829 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5124 0.09857 0.09393 -0.0688 1.0000 0.0159
-13.250 -0.5369 0.08693 0.08220 -0.0772 0.9918 0.0153
-13.000 -0.5655 0.07708 0.07218 -0.0846 0.9852 0.0151
-12.750 -0.5864 0.07026 0.06512 -0.0890 0.9796 0.0149
-12.500 -0.6040 0.06477 0.05937 -0.0915 0.9738 0.0147
-12.250 -0.6205 0.05965 0.05392 -0.0929 0.9692 0.0147
-12.000 -0.6347 0.05550 0.04944 -0.0926 0.9625 0.0147
-11.750 -0.6426 0.05176 0.04534 -0.0921 0.9574 0.0149
-11.500 -0.6482 0.04869 0.04191 -0.0905 0.9512 0.0152
-11.250 -0.6488 0.04589 0.03869 -0.0891 0.9458 0.0158
-11.000 -0.6451 0.04352 0.03591 -0.0875 0.9410 0.0167
-10.750 -0.6411 0.04157 0.03352 -0.0852 0.9354 0.0177
-10.500 -0.6284 0.03901 0.03072 -0.0843 0.9319 0.0184
-10.250 -0.6137 0.03717 0.02873 -0.0837 0.9289 0.0197
-10.000 -0.5996 0.03563 0.02701 -0.0823 0.9244 0.0211
-9.750 -0.5783 0.03392 0.02506 -0.0818 0.9211 0.0229
-9.500 -0.5554 0.03259 0.02346 -0.0815 0.9182 0.0254
-9.250 -0.5376 0.03124 0.02207 -0.0809 0.9156 0.0294
-9.000 -0.5219 0.03024 0.02094 -0.0794 0.9116 0.0339
-8.750 -0.5064 0.02925 0.01987 -0.0781 0.9081 0.0393
-8.500 -0.4896 0.02838 0.01887 -0.0770 0.9052 0.0459
-8.250 -0.4737 0.02742 0.01788 -0.0757 0.9026 0.0542
-8.000 -0.4598 0.02667 0.01710 -0.0740 0.8997 0.0650
-7.750 -0.4478 0.02605 0.01647 -0.0720 0.8958 0.0774
-7.500 -0.4335 0.02540 0.01587 -0.0703 0.8925 0.0966
-7.250 -0.4179 0.02469 0.01527 -0.0688 0.8899 0.1238
-7.000 -0.4013 0.02396 0.01473 -0.0676 0.8878 0.1643
-6.750 -0.3924 0.02347 0.01450 -0.0650 0.8842 0.2147
-6.500 -0.3848 0.02289 0.01423 -0.0622 0.8808 0.2842
-6.250 -0.3794 0.02218 0.01400 -0.0588 0.8778 0.3763
-5.750 -0.2757 0.02444 0.01739 -0.0628 0.8778 0.6541
-5.500 -0.2564 0.02495 0.01776 -0.0608 0.8756 0.6853
-5.250 -0.2442 0.02529 0.01792 -0.0579 0.8730 0.7096
-5.000 -0.2310 0.02609 0.01861 -0.0549 0.8694 0.7269
-4.750 -0.2135 0.02680 0.01920 -0.0527 0.8667 0.7430
-4.500 -0.1905 0.02747 0.01973 -0.0514 0.8646 0.7572
-4.250 -0.1629 0.02811 0.02022 -0.0510 0.8630 0.7695
-4.000 -0.1354 0.02860 0.02056 -0.0508 0.8615 0.7808
-3.750 -0.1114 0.02892 0.02075 -0.0500 0.8600 0.7920
-3.500 -0.0848 0.02951 0.02125 -0.0499 0.8574 0.7993
-3.250 -0.0703 0.02999 0.02166 -0.0477 0.8543 0.8078
-3.000 -0.0643 0.03032 0.02193 -0.0441 0.8512 0.8181
-2.750 -0.0257 0.03050 0.02199 -0.0464 0.8500 0.8214
-2.500 0.0017 0.03060 0.02201 -0.0468 0.8484 0.8269
-2.250 0.0208 0.03063 0.02197 -0.0456 0.8467 0.8335
-2.000 0.0542 0.03068 0.02194 -0.0472 0.8458 0.8368
-1.750 0.0325 0.03151 0.02279 -0.0386 0.8391 0.8467
-1.500 0.0619 0.03162 0.02285 -0.0395 0.8371 0.8496
-1.250 0.0846 0.03173 0.02292 -0.0392 0.8352 0.8539
-1.000 0.0948 0.03179 0.02294 -0.0364 0.8331 0.8603
-0.750 0.1293 0.03175 0.02287 -0.0383 0.8321 0.8623
-0.500 0.1151 0.03256 0.02371 -0.0313 0.8253 0.8690
-0.250 0.1200 0.03270 0.02383 -0.0276 0.8218 0.8746
0.000 0.1511 0.03273 0.02385 -0.0289 0.8202 0.8767
0.250 0.1806 0.03273 0.02385 -0.0298 0.8188 0.8791
0.750 0.1698 0.03345 0.02459 -0.0186 0.8078 0.8900
1.000 0.2001 0.03346 0.02462 -0.0198 0.8060 0.8920
1.250 0.2304 0.03343 0.02463 -0.0209 0.8045 0.8941
1.500 0.1926 0.03393 0.02512 -0.0092 0.7949 0.9022
1.750 0.2233 0.03393 0.02517 -0.0104 0.7927 0.9036
2.000 0.2568 0.03391 0.02519 -0.0121 0.7909 0.9050
2.250 0.2482 0.03432 0.02564 -0.0062 0.7828 0.9099
2.500 0.2628 0.03427 0.02562 -0.0041 0.7791 0.9132
2.750 0.2879 0.03414 0.02556 -0.0039 0.7768 0.9157
3.000 0.2921 0.03450 0.02598 -0.0006 0.7682 0.9186
3.250 0.3222 0.03440 0.02596 -0.0015 0.7649 0.9200
3.500 0.3580 0.03420 0.02589 -0.0032 0.7627 0.9212
3.750 0.3479 0.03441 0.02613 0.0032 0.7524 0.9266
4.000 0.3726 0.03400 0.02580 0.0039 0.7491 0.9290
4.250 0.3857 0.03409 0.02599 0.0059 0.7390 0.9311
4.500 0.4321 0.03334 0.02539 0.0029 0.7354 0.9314
4.750 0.4486 0.03310 0.02528 0.0047 0.7239 0.9340
5.000 0.4665 0.03264 0.02493 0.0066 0.7126 0.9366
5.250 0.4841 0.03198 0.02438 0.0089 0.7017 0.9394
5.500 0.5061 0.03094 0.02346 0.0109 0.6919 0.9421
5.750 0.5221 0.03055 0.02321 0.0129 0.6763 0.9445
6.000 0.5379 0.03027 0.02308 0.0147 0.6587 0.9471
6.500 0.5487 0.03004 0.02311 0.0220 0.6173 0.9546
6.750 0.5651 0.02962 0.02282 0.0241 0.5877 0.9574
7.000 0.6392 0.02560 0.01844 0.0216 0.4844 0.9563
7.250 0.6563 0.02590 0.01788 0.0237 0.3532 0.9579
7.500 0.6615 0.02700 0.01856 0.0263 0.2732 0.9607
7.750 0.6689 0.02793 0.01917 0.0285 0.2142 0.9635
8.000 0.6763 0.02876 0.01976 0.0310 0.1706 0.9668
8.250 0.6856 0.02956 0.02039 0.0331 0.1380 0.9700
8.500 0.7033 0.03046 0.02119 0.0334 0.1120 0.9719
8.750 0.7191 0.03142 0.02206 0.0340 0.0934 0.9743
9.000 0.7336 0.03235 0.02296 0.0350 0.0799 0.9769
9.250 0.7468 0.03324 0.02394 0.0363 0.0704 0.9797
9.500 0.7587 0.03425 0.02497 0.0377 0.0629 0.9825
9.750 0.7755 0.03532 0.02611 0.0380 0.0550 0.9844
10.000 0.7936 0.03644 0.02737 0.0383 0.0494 0.9865
10.250 0.8096 0.03761 0.02859 0.0387 0.0436 0.9890
10.500 0.8268 0.03886 0.02998 0.0392 0.0388 0.9915
10.750 0.8445 0.04018 0.03144 0.0397 0.0352 0.9937
11.000 0.8602 0.04165 0.03295 0.0399 0.0320 0.9959
11.250 0.8784 0.04326 0.03480 0.0402 0.0284 0.9980
11.500 0.8967 0.04509 0.03687 0.0405 0.0258 0.9999
11.750 0.8962 0.04630 0.03820 0.0437 0.0242 1.0000
12.000 0.8934 0.04755 0.03953 0.0470 0.0231 1.0000
12.250 0.8892 0.04923 0.04127 0.0503 0.0218 1.0000
12.500 0.8829 0.05069 0.04301 0.0540 0.0207 1.0000
12.750 0.8763 0.05244 0.04501 0.0576 0.0199 1.0000
13.000 0.8666 0.05433 0.04714 0.0613 0.0190 1.0000
13.250 0.8560 0.05645 0.04947 0.0647 0.0187 1.0000
13.500 0.8416 0.05902 0.05227 0.0680 0.0180 1.0000
13.750 0.8280 0.06175 0.05520 0.0705 0.0178 1.0000
14.000 0.8136 0.06479 0.05846 0.0725 0.0176 1.0000
14.250 0.7973 0.06846 0.06233 0.0737 0.0175 1.0000
14.500 0.7807 0.07234 0.06641 0.0742 0.0170 1.0000
14.750 0.7588 0.07761 0.07192 0.0738 0.0175 1.0000
15.000 0.7364 0.08335 0.07785 0.0724 0.0174 1.0000
15.250 0.7112 0.09028 0.08498 0.0696 0.0173 1.0000
15.500 0.6795 0.09969 0.09459 0.0647 0.0180 1.0000
15.750 0.6464 0.11123 0.10622 0.0581 0.0188 1.0000
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