NREL's S828 Airfoil (s828-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S828 Airfoil (s828-nr) Reynolds number: 100,000 Max Cl/Cd: 28.49 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s828-nr-100000-n5.txt Download as CSV file: xf-s828-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S828 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2754 0.09707 0.09200 -0.1067 0.9301 0.0181
-12.000 -0.2783 0.09206 0.08701 -0.1092 0.9241 0.0179
-11.750 -0.2853 0.08518 0.08013 -0.1133 0.9192 0.0177
-11.500 -0.2932 0.07828 0.07319 -0.1181 0.9142 0.0174
-11.250 -0.3115 0.07177 0.06659 -0.1220 0.9077 0.0172
-11.000 -0.3291 0.06682 0.06150 -0.1239 0.9026 0.0170
-10.750 -0.3449 0.06338 0.05792 -0.1237 0.8962 0.0168
-10.500 -0.3617 0.06001 0.05439 -0.1227 0.8910 0.0166
-10.250 -0.3820 0.05664 0.05080 -0.1202 0.8859 0.0165
-10.000 -0.3974 0.05400 0.04796 -0.1172 0.8804 0.0164
-9.750 -0.4106 0.05144 0.04516 -0.1137 0.8761 0.0162
-9.500 -0.4260 0.04899 0.04243 -0.1091 0.8714 0.0163
-9.250 -0.4368 0.04720 0.04041 -0.1044 0.8665 0.0162
-9.000 -0.4451 0.04486 0.03772 -0.0997 0.8628 0.0162
-8.500 -0.4477 0.04061 0.03276 -0.0918 0.8553 0.0164
-8.250 -0.4421 0.03857 0.03034 -0.0886 0.8520 0.0166
-8.000 -0.4292 0.03639 0.02771 -0.0864 0.8497 0.0169
-7.750 -0.4077 0.03407 0.02495 -0.0855 0.8481 0.0176
-7.500 -0.3793 0.03213 0.02264 -0.0858 0.8469 0.0183
-7.250 -0.3545 0.03057 0.02099 -0.0860 0.8457 0.0203
-7.000 -0.3384 0.02987 0.02020 -0.0845 0.8426 0.0221
-6.750 -0.3153 0.02894 0.01907 -0.0839 0.8404 0.0254
-6.500 -0.2957 0.02777 0.01786 -0.0829 0.8382 0.0281
-6.250 -0.2788 0.02715 0.01714 -0.0814 0.8360 0.0329
-6.000 -0.2628 0.02631 0.01626 -0.0795 0.8341 0.0414
-5.750 -0.2462 0.02561 0.01554 -0.0778 0.8326 0.0543
-5.500 -0.2382 0.02537 0.01531 -0.0746 0.8300 0.0725
-5.250 -0.2400 0.02542 0.01550 -0.0697 0.8262 0.0905
-5.000 -0.2317 0.02505 0.01538 -0.0667 0.8237 0.1359
-4.750 -0.2177 0.02436 0.01519 -0.0648 0.8219 0.2307
-4.500 -0.0959 0.02492 0.01781 -0.0779 0.8263 0.7212
-4.250 -0.0947 0.02561 0.01840 -0.0727 0.8232 0.7537
-4.000 -0.0873 0.02625 0.01889 -0.0685 0.8208 0.7802
-3.750 -0.0759 0.02690 0.01938 -0.0650 0.8190 0.8027
-3.500 -0.0368 0.02786 0.02009 -0.0662 0.8184 0.8210
-3.250 0.0120 0.02883 0.02085 -0.0693 0.8182 0.8394
-3.000 0.0543 0.02938 0.02122 -0.0718 0.8178 0.8529
-2.750 0.0541 0.03049 0.02229 -0.0672 0.8136 0.8644
-2.500 0.0588 0.03110 0.02283 -0.0633 0.8102 0.8751
-2.250 0.0935 0.03123 0.02282 -0.0653 0.8088 0.8795
-2.000 0.1008 0.03155 0.02306 -0.0619 0.8067 0.8884
-1.750 0.1359 0.03159 0.02298 -0.0640 0.8059 0.8915
-1.500 0.1638 0.03168 0.02297 -0.0648 0.8049 0.8957
-1.250 0.1533 0.03250 0.02378 -0.0585 0.8004 0.9040
-1.000 0.1556 0.03318 0.02444 -0.0547 0.7965 0.9097
-0.750 0.1565 0.03351 0.02472 -0.0503 0.7934 0.9166
-0.500 0.1879 0.03353 0.02467 -0.0517 0.7921 0.9188
0.000 0.2245 0.03397 0.02502 -0.0498 0.7880 0.9263
0.500 0.2300 0.03492 0.02596 -0.0424 0.7795 0.9352
0.750 0.2536 0.03503 0.02604 -0.0424 0.7778 0.9377
1.000 0.2773 0.03509 0.02607 -0.0422 0.7763 0.9404
1.500 0.2821 0.03608 0.02708 -0.0350 0.7666 0.9477
1.750 0.3061 0.03619 0.02720 -0.0350 0.7644 0.9496
2.000 0.3333 0.03625 0.02726 -0.0355 0.7627 0.9514
2.500 0.3390 0.03708 0.02814 -0.0282 0.7522 0.9581
2.750 0.3674 0.03716 0.02825 -0.0291 0.7499 0.9593
3.000 0.3980 0.03715 0.02829 -0.0301 0.7482 0.9602
3.250 0.3962 0.03780 0.02899 -0.0262 0.7401 0.9633
3.500 0.4204 0.03788 0.02912 -0.0261 0.7368 0.9651
3.750 0.4488 0.03784 0.02913 -0.0266 0.7347 0.9663
4.250 0.4688 0.03838 0.02982 -0.0217 0.7226 0.9708
4.500 0.5033 0.03823 0.02976 -0.0233 0.7204 0.9716
4.750 0.5096 0.03876 0.03037 -0.0208 0.7110 0.9738
5.000 0.5403 0.03854 0.03029 -0.0215 0.7077 0.9747
5.500 0.5797 0.03851 0.03047 -0.0197 0.6944 0.9778
5.750 0.6176 0.03781 0.02993 -0.0210 0.6912 0.9786
6.000 0.6255 0.03794 0.03019 -0.0182 0.6800 0.9813
6.250 0.6382 0.03787 0.03024 -0.0161 0.6691 0.9833
6.500 0.6650 0.03722 0.02974 -0.0158 0.6599 0.9843
6.750 0.6975 0.03609 0.02880 -0.0159 0.6507 0.9853
7.750 0.7461 0.03592 0.02926 -0.0078 0.5748 0.9944
8.000 0.7712 0.03501 0.02849 -0.0069 0.5451 0.9960
8.250 0.8459 0.02969 0.02259 -0.0080 0.4227 0.9951
8.500 0.8489 0.03057 0.02280 -0.0046 0.3243 0.9972
8.750 0.8495 0.03202 0.02379 -0.0018 0.2504 0.9995
9.000 0.8475 0.03317 0.02462 0.0019 0.1977 1.0000
9.250 0.8454 0.03416 0.02536 0.0057 0.1572 1.0000
9.500 0.8449 0.03510 0.02611 0.0093 0.1262 1.0000
9.750 0.8449 0.03602 0.02689 0.0128 0.1031 1.0000
10.000 0.8452 0.03694 0.02773 0.0162 0.0859 1.0000
10.250 0.8455 0.03785 0.02858 0.0196 0.0738 1.0000
10.500 0.8455 0.03876 0.02949 0.0230 0.0647 1.0000
10.750 0.8456 0.03967 0.03046 0.0264 0.0585 1.0000
11.000 0.8455 0.04060 0.03147 0.0297 0.0533 1.0000
11.250 0.8456 0.04159 0.03250 0.0329 0.0482 1.0000
11.500 0.8477 0.04252 0.03352 0.0358 0.0436 1.0000
11.750 0.8484 0.04374 0.03474 0.0386 0.0405 1.0000
12.000 0.8545 0.04490 0.03602 0.0409 0.0372 1.0000
12.250 0.8617 0.04606 0.03728 0.0427 0.0335 1.0000
12.500 0.8682 0.04749 0.03875 0.0443 0.0308 1.0000
12.750 0.8792 0.04901 0.04039 0.0457 0.0282 1.0000
13.000 0.8899 0.05053 0.04211 0.0469 0.0253 1.0000
13.250 0.8965 0.05227 0.04395 0.0480 0.0230 1.0000
13.500 0.9059 0.05441 0.04614 0.0490 0.0214 1.0000
13.750 0.9130 0.05666 0.04875 0.0501 0.0195 1.0000
14.000 0.9182 0.05906 0.05142 0.0511 0.0183 1.0000
14.250 0.9196 0.06157 0.05415 0.0520 0.0173 1.0000
14.500 0.9173 0.06429 0.05704 0.0527 0.0161 1.0000
14.750 0.9153 0.06731 0.06025 0.0534 0.0156 1.0000
15.000 0.9097 0.07090 0.06399 0.0538 0.0151 1.0000
15.250 0.9018 0.07489 0.06818 0.0541 0.0148 1.0000
15.500 0.8860 0.07979 0.07341 0.0540 0.0144 1.0000
15.750 0.8753 0.08433 0.07816 0.0534 0.0145 1.0000
16.000 0.8575 0.08996 0.08407 0.0520 0.0144 1.0000
16.250 0.8403 0.09592 0.09026 0.0500 0.0143 1.0000
16.500 0.8199 0.10292 0.09749 0.0470 0.0143 1.0000
16.750 0.8019 0.11004 0.10479 0.0435 0.0144 1.0000
17.000 0.7817 0.11827 0.11317 0.0389 0.0145 1.0000
17.250 0.7627 0.12698 0.12202 0.0338 0.0146 1.0000
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