NREL's S829 Airfoil (s829-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S829 Airfoil (s829-nr) Reynolds number: 500,000 Max Cl/Cd: 62.25 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s829-nr-500000-n5.txt Download as CSV file: xf-s829-nr-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7436 0.07071 0.06738 -0.0805 0.9089 0.0026
-15.500 -0.7662 0.06372 0.06015 -0.0836 0.9005 0.0026
-15.250 -0.7811 0.05862 0.05485 -0.0854 0.8928 0.0026
-15.000 -0.7903 0.05473 0.05076 -0.0861 0.8861 0.0026
-14.750 -0.8119 0.04977 0.04556 -0.0861 0.8795 0.0025
-14.250 -0.8374 0.04276 0.03808 -0.0842 0.8685 0.0027
-14.000 -0.8398 0.04053 0.03567 -0.0829 0.8635 0.0027
-13.750 -0.8451 0.03807 0.03300 -0.0811 0.8593 0.0028
-13.500 -0.8458 0.03605 0.03081 -0.0795 0.8553 0.0028
-13.250 -0.8418 0.03446 0.02905 -0.0780 0.8514 0.0027
-13.000 -0.8432 0.03246 0.02687 -0.0758 0.8478 0.0029
-12.750 -0.8381 0.03097 0.02519 -0.0741 0.8447 0.0029
-12.500 -0.8306 0.02964 0.02373 -0.0725 0.8415 0.0029
-12.250 -0.8213 0.02850 0.02247 -0.0710 0.8384 0.0031
-12.000 -0.8106 0.02746 0.02131 -0.0695 0.8354 0.0032
-11.750 -0.8011 0.02630 0.02000 -0.0678 0.8327 0.0032
-11.500 -0.7879 0.02542 0.01902 -0.0665 0.8300 0.0034
-11.250 -0.7754 0.02444 0.01793 -0.0650 0.8272 0.0034
-11.000 -0.7607 0.02365 0.01705 -0.0638 0.8246 0.0036
-10.750 -0.7471 0.02275 0.01603 -0.0623 0.8222 0.0037
-10.500 -0.7305 0.02214 0.01533 -0.0612 0.8201 0.0039
-10.250 -0.7140 0.02150 0.01459 -0.0601 0.8182 0.0042
-10.000 -0.6985 0.02072 0.01369 -0.0588 0.8161 0.0044
-9.750 -0.6812 0.02009 0.01299 -0.0577 0.8140 0.0048
-9.500 -0.6643 0.01943 0.01225 -0.0565 0.8118 0.0049
-9.250 -0.6477 0.01874 0.01150 -0.0553 0.8098 0.0054
-9.000 -0.6298 0.01816 0.01086 -0.0541 0.8079 0.0065
-8.750 -0.6112 0.01766 0.01027 -0.0531 0.8061 0.0069
-8.500 -0.5929 0.01713 0.00967 -0.0519 0.8043 0.0083
-8.250 -0.5741 0.01663 0.00917 -0.0509 0.8024 0.0105
-8.000 -0.5541 0.01623 0.00869 -0.0501 0.8005 0.0118
-7.750 -0.5351 0.01577 0.00825 -0.0490 0.7987 0.0162
-7.500 -0.5155 0.01536 0.00784 -0.0481 0.7970 0.0208
-7.250 -0.4953 0.01500 0.00748 -0.0472 0.7953 0.0265
-7.000 -0.4758 0.01461 0.00711 -0.0462 0.7937 0.0345
-6.750 -0.4564 0.01423 0.00676 -0.0452 0.7923 0.0460
-6.500 -0.4366 0.01388 0.00643 -0.0442 0.7909 0.0567
-6.250 -0.4170 0.01353 0.00610 -0.0432 0.7896 0.0714
-6.000 -0.3976 0.01317 0.00581 -0.0422 0.7880 0.0893
-5.750 -0.3784 0.01281 0.00553 -0.0411 0.7864 0.1098
-5.500 -0.3606 0.01240 0.00524 -0.0397 0.7847 0.1402
-5.250 -0.3453 0.01190 0.00494 -0.0379 0.7829 0.1849
-5.000 -0.3303 0.01143 0.00464 -0.0360 0.7812 0.2295
-4.750 -0.3162 0.01097 0.00435 -0.0339 0.7797 0.2763
-4.500 -0.3074 0.01039 0.00400 -0.0307 0.7782 0.3405
-4.250 -0.3026 0.00981 0.00367 -0.0267 0.7768 0.4058
-4.000 -0.3038 0.00931 0.00343 -0.0212 0.7750 0.4704
-3.750 -0.3108 0.00876 0.00323 -0.0144 0.7730 0.5477
-3.500 -0.3146 0.00816 0.00308 -0.0081 0.7710 0.6427
-3.250 -0.2994 0.00801 0.00321 -0.0055 0.7695 0.7163
-3.000 -0.2756 0.00805 0.00328 -0.0047 0.7681 0.7442
-2.750 -0.2505 0.00809 0.00329 -0.0043 0.7668 0.7583
-2.500 -0.2246 0.00814 0.00331 -0.0040 0.7657 0.7692
-2.250 -0.1990 0.00821 0.00334 -0.0037 0.7647 0.7797
-2.000 -0.1744 0.00827 0.00336 -0.0032 0.7637 0.7895
-1.750 -0.1464 0.00849 0.00357 -0.0032 0.7628 0.8005
-1.500 -0.1180 0.00874 0.00383 -0.0033 0.7619 0.8095
-1.250 -0.0924 0.00884 0.00392 -0.0030 0.7606 0.8154
-1.000 -0.0673 0.00883 0.00387 -0.0028 0.7591 0.8183
-0.750 -0.0384 0.00885 0.00389 -0.0033 0.7578 0.8195
-0.500 -0.0099 0.00887 0.00391 -0.0038 0.7565 0.8207
-0.250 0.0184 0.00890 0.00392 -0.0042 0.7554 0.8221
0.000 0.0464 0.00891 0.00393 -0.0046 0.7543 0.8235
0.250 0.0741 0.00892 0.00393 -0.0049 0.7531 0.8250
0.500 0.1015 0.00891 0.00392 -0.0051 0.7519 0.8267
0.750 0.1288 0.00891 0.00390 -0.0053 0.7508 0.8286
1.000 0.1558 0.00890 0.00387 -0.0056 0.7498 0.8304
1.250 0.1832 0.00889 0.00385 -0.0058 0.7489 0.8319
1.500 0.2111 0.00893 0.00393 -0.0062 0.7475 0.8329
1.750 0.2384 0.00898 0.00403 -0.0064 0.7459 0.8341
2.000 0.2656 0.00903 0.00412 -0.0067 0.7442 0.8353
2.250 0.2929 0.00905 0.00419 -0.0069 0.7421 0.8364
2.500 0.3206 0.00904 0.00420 -0.0072 0.7396 0.8377
2.750 0.3505 0.00889 0.00402 -0.0077 0.7348 0.8389
3.000 0.3737 0.00873 0.00390 -0.0069 0.7242 0.8407
3.250 0.3981 0.00861 0.00381 -0.0063 0.7140 0.8426
3.500 0.4238 0.00852 0.00371 -0.0061 0.7059 0.8443
3.750 0.4477 0.00846 0.00368 -0.0055 0.6954 0.8458
4.000 0.4722 0.00845 0.00372 -0.0051 0.6846 0.8469
4.250 0.4967 0.00845 0.00377 -0.0046 0.6728 0.8480
4.500 0.5192 0.00846 0.00378 -0.0037 0.6530 0.8493
4.750 0.5335 0.00857 0.00375 -0.0011 0.6028 0.8513
5.000 0.5244 0.00914 0.00394 0.0062 0.5267 0.8547
5.250 0.5066 0.00973 0.00425 0.0149 0.4676 0.8587
5.500 0.4960 0.01056 0.00484 0.0217 0.4089 0.8616
5.750 0.4930 0.01136 0.00544 0.0269 0.3565 0.8643
6.000 0.4951 0.01211 0.00599 0.0309 0.3081 0.8672
6.250 0.5011 0.01280 0.00652 0.0341 0.2648 0.8702
6.500 0.5073 0.01353 0.00704 0.0371 0.2186 0.8729
6.750 0.5176 0.01416 0.00752 0.0394 0.1818 0.8749
7.000 0.5295 0.01475 0.00800 0.0415 0.1507 0.8769
7.250 0.5430 0.01530 0.00846 0.0432 0.1257 0.8791
7.500 0.5574 0.01583 0.00891 0.0448 0.1053 0.8814
7.750 0.5734 0.01631 0.00934 0.0461 0.0908 0.8839
8.000 0.5896 0.01679 0.00980 0.0474 0.0779 0.8864
8.250 0.6056 0.01728 0.01027 0.0487 0.0660 0.8885
8.750 0.6382 0.01826 0.01124 0.0511 0.0471 0.8926
9.000 0.6546 0.01877 0.01174 0.0523 0.0403 0.8950
9.250 0.6712 0.01928 0.01226 0.0533 0.0350 0.8975
9.500 0.6872 0.01984 0.01282 0.0545 0.0306 0.9000
9.750 0.7044 0.02032 0.01335 0.0554 0.0272 0.9024
10.000 0.7201 0.02088 0.01396 0.0566 0.0239 0.9049
10.250 0.7354 0.02148 0.01459 0.0578 0.0208 0.9077
10.500 0.7517 0.02203 0.01518 0.0588 0.0181 0.9105
10.750 0.7664 0.02271 0.01585 0.0599 0.0148 0.9134
11.000 0.7825 0.02329 0.01649 0.0608 0.0133 0.9161
11.250 0.7972 0.02393 0.01715 0.0619 0.0105 0.9188
11.500 0.8112 0.02466 0.01792 0.0631 0.0092 0.9220
11.750 0.8258 0.02537 0.01871 0.0642 0.0086 0.9257
12.000 0.8400 0.02610 0.01946 0.0651 0.0068 0.9293
12.250 0.8529 0.02693 0.02037 0.0663 0.0057 0.9329
12.500 0.8668 0.02772 0.02125 0.0672 0.0050 0.9369
12.750 0.8795 0.02861 0.02223 0.0683 0.0046 0.9412
13.000 0.8921 0.02960 0.02330 0.0692 0.0041 0.9454
13.250 0.9050 0.03064 0.02442 0.0699 0.0037 0.9502
13.500 0.9164 0.03186 0.02575 0.0707 0.0030 0.9556
13.750 0.9315 0.03307 0.02707 0.0706 0.0028 0.9604
14.000 0.9468 0.03441 0.02853 0.0702 0.0026 0.9654
14.250 0.9609 0.03598 0.03023 0.0698 0.0028 0.9705
14.500 0.9760 0.03761 0.03198 0.0689 0.0024 0.9751
14.750 0.9899 0.03932 0.03380 0.0680 0.0020 0.9803
15.000 1.0019 0.04124 0.03587 0.0672 0.0023 0.9872
15.250 1.0064 0.04376 0.03853 0.0670 0.0019 1.0000
15.500 1.0073 0.04591 0.04079 0.0678 0.0019 1.0000
15.750 1.0058 0.04840 0.04341 0.0686 0.0018 1.0000
16.000 1.0062 0.05079 0.04592 0.0690 0.0019 1.0000
16.250 1.0022 0.05378 0.04905 0.0693 0.0018 1.0000
16.500 0.9974 0.05702 0.05243 0.0694 0.0018 1.0000
16.750 0.9928 0.06041 0.05599 0.0691 0.0016 1.0000
17.000 0.9880 0.06398 0.05966 0.0685 0.0018 1.0000
17.250 0.9774 0.06854 0.06440 0.0674 0.0017 1.0000
17.500 0.9676 0.07324 0.06924 0.0658 0.0017 1.0000
17.750 0.9538 0.07888 0.07506 0.0637 0.0016 1.0000
18.000 0.9444 0.08412 0.08042 0.0613 0.0017 1.0000
18.250 0.9198 0.09231 0.08882 0.0573 0.0016 1.0000
18.500 0.8983 0.10049 0.09717 0.0531 0.0016 1.0000
18.750 0.8749 0.10946 0.10630 0.0484 0.0017 1.0000
19.000 0.8470 0.11960 0.11657 0.0431 0.0018 1.0000
19.250 0.8169 0.13060 0.12772 0.0375 0.0018 1.0000
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