NREL's S829 Airfoil (s829-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S829 Airfoil (s829-nr) Reynolds number: 1,000,000 Max Cl/Cd: 88.23 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s829-nr-1000000.txt Download as CSV file: xf-s829-nr-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.6663 0.10146 0.09958 -0.0616 0.9667 0.0028
-16.250 -0.6844 0.09053 0.08849 -0.0690 0.9585 0.0028
-16.000 -0.7102 0.07914 0.07689 -0.0768 0.9454 0.0028
-15.750 -0.6989 0.07713 0.07479 -0.0781 0.9268 0.0027
-15.500 -0.7172 0.06997 0.06743 -0.0820 0.9143 0.0027
-15.250 -0.7331 0.06405 0.06133 -0.0848 0.9037 0.0027
-15.000 -0.7596 0.05738 0.05443 -0.0870 0.8951 0.0027
-14.750 -0.7382 0.05748 0.05453 -0.0870 0.8879 0.0026
-14.500 -0.8116 0.04657 0.04311 -0.0870 0.8808 0.0027
-14.250 -0.8259 0.04310 0.03941 -0.0857 0.8750 0.0027
-14.000 -0.8402 0.03978 0.03587 -0.0839 0.8699 0.0028
-13.750 -0.8441 0.03753 0.03346 -0.0822 0.8651 0.0028
-13.500 -0.8529 0.03493 0.03063 -0.0798 0.8606 0.0028
-13.250 -0.8196 0.03627 0.03211 -0.0807 0.8570 0.0026
-13.000 -0.8655 0.03005 0.02532 -0.0745 0.8525 0.0030
-12.750 -0.8528 0.02933 0.02450 -0.0733 0.8489 0.0028
-12.500 -0.8417 0.02849 0.02355 -0.0720 0.8455 0.0027
-12.250 -0.8468 0.02600 0.02084 -0.0687 0.8425 0.0031
-12.000 -0.8333 0.02534 0.02014 -0.0676 0.8396 0.0034
-11.750 -0.8254 0.02395 0.01858 -0.0655 0.8367 0.0033
-11.500 -0.8102 0.02336 0.01793 -0.0644 0.8340 0.0036
-11.250 -0.7984 0.02235 0.01679 -0.0627 0.8314 0.0036
-11.000 -0.7830 0.02162 0.01599 -0.0615 0.8292 0.0038
-10.750 -0.7701 0.02061 0.01487 -0.0598 0.8268 0.0039
-10.500 -0.7536 0.01998 0.01417 -0.0586 0.8245 0.0040
-10.250 -0.7376 0.01929 0.01340 -0.0573 0.8222 0.0041
-10.000 -0.7233 0.01846 0.01243 -0.0557 0.8199 0.0042
-9.750 -0.7040 0.01806 0.01198 -0.0548 0.8176 0.0045
-9.500 -0.6860 0.01752 0.01138 -0.0537 0.8157 0.0045
-9.250 -0.6686 0.01692 0.01071 -0.0525 0.8138 0.0046
-9.000 -0.6574 0.01582 0.00948 -0.0501 0.8117 0.0051
-8.750 -0.6389 0.01532 0.00891 -0.0490 0.8098 0.0052
-8.500 -0.6207 0.01480 0.00835 -0.0478 0.8080 0.0060
-8.250 -0.6009 0.01441 0.00791 -0.0468 0.8063 0.0071
-8.000 -0.5798 0.01414 0.00760 -0.0461 0.8044 0.0072
-7.750 -0.5623 0.01358 0.00702 -0.0447 0.8029 0.0118
-7.500 -0.5435 0.01312 0.00660 -0.0435 0.8014 0.0176
-7.250 -0.5242 0.01273 0.00625 -0.0425 0.7998 0.0243
-7.000 -0.5039 0.01239 0.00593 -0.0415 0.7981 0.0314
-6.750 -0.4833 0.01208 0.00564 -0.0406 0.7964 0.0396
-6.500 -0.4632 0.01177 0.00536 -0.0396 0.7948 0.0501
-6.250 -0.4446 0.01139 0.00507 -0.0384 0.7932 0.0684
-6.000 -0.4257 0.01105 0.00479 -0.0372 0.7917 0.0900
-5.750 -0.4085 0.01068 0.00454 -0.0356 0.7900 0.1200
-5.500 -0.3917 0.01026 0.00428 -0.0340 0.7888 0.1557
-5.250 -0.3774 0.00978 0.00400 -0.0319 0.7874 0.2017
-5.000 -0.3640 0.00931 0.00373 -0.0296 0.7858 0.2508
-4.750 -0.3543 0.00877 0.00344 -0.0265 0.7842 0.3123
-4.500 -0.3526 0.00815 0.00314 -0.0218 0.7824 0.3907
-4.250 -0.3586 0.00760 0.00290 -0.0152 0.7806 0.4708
-4.000 -0.3654 0.00692 0.00261 -0.0084 0.7787 0.5704
-3.750 -0.3661 0.00633 0.00243 -0.0027 0.7768 0.6705
-3.500 -0.3484 0.00618 0.00245 -0.0007 0.7756 0.7256
-3.250 -0.3240 0.00616 0.00247 -0.0001 0.7746 0.7504
-3.000 -0.2978 0.00618 0.00248 0.0000 0.7735 0.7643
-2.750 -0.2711 0.00622 0.00250 0.0000 0.7724 0.7752
-2.500 -0.2435 0.00628 0.00256 -0.0001 0.7713 0.7840
-2.250 -0.2166 0.00632 0.00256 -0.0001 0.7702 0.7907
-2.000 -0.1876 0.00637 0.00261 -0.0006 0.7690 0.7954
-1.750 -0.1598 0.00644 0.00265 -0.0008 0.7678 0.8017
-1.500 -0.1314 0.00650 0.00270 -0.0011 0.7668 0.8067
-1.250 -0.1021 0.00662 0.00282 -0.0015 0.7659 0.8118
-1.000 -0.0746 0.00677 0.00295 -0.0016 0.7649 0.8193
-0.750 -0.0438 0.00700 0.00322 -0.0022 0.7640 0.8250
-0.500 -0.0154 0.00714 0.00334 -0.0025 0.7629 0.8291
-0.250 0.0122 0.00718 0.00335 -0.0029 0.7618 0.8311
0.000 0.0406 0.00716 0.00333 -0.0033 0.7608 0.8326
0.250 0.0696 0.00715 0.00334 -0.0039 0.7598 0.8337
0.500 0.0987 0.00716 0.00337 -0.0045 0.7587 0.8349
0.750 0.1276 0.00718 0.00340 -0.0051 0.7574 0.8360
1.000 0.1564 0.00719 0.00343 -0.0056 0.7562 0.8372
1.250 0.1853 0.00721 0.00346 -0.0062 0.7550 0.8385
1.500 0.2141 0.00721 0.00346 -0.0067 0.7535 0.8399
1.750 0.2432 0.00719 0.00343 -0.0073 0.7517 0.8412
2.000 0.2720 0.00715 0.00336 -0.0077 0.7478 0.8425
2.250 0.2990 0.00696 0.00320 -0.0077 0.7412 0.8439
2.500 0.3280 0.00685 0.00303 -0.0081 0.7351 0.8452
2.750 0.3549 0.00676 0.00298 -0.0082 0.7303 0.8465
3.000 0.3830 0.00666 0.00291 -0.0085 0.7250 0.8476
3.250 0.4113 0.00662 0.00288 -0.0088 0.7197 0.8486
3.500 0.4385 0.00658 0.00290 -0.0090 0.7145 0.8497
3.750 0.4663 0.00655 0.00288 -0.0092 0.7088 0.8509
4.000 0.4934 0.00655 0.00292 -0.0094 0.7032 0.8522
4.250 0.5196 0.00652 0.00290 -0.0092 0.6929 0.8537
4.500 0.5449 0.00651 0.00292 -0.0090 0.6801 0.8552
4.750 0.5697 0.00653 0.00294 -0.0087 0.6650 0.8567
5.000 0.5876 0.00666 0.00296 -0.0068 0.6209 0.8583
5.250 0.5794 0.00734 0.00322 0.0002 0.5273 0.8610
5.500 0.5628 0.00799 0.00358 0.0089 0.4559 0.8641
5.750 0.5535 0.00869 0.00407 0.0158 0.3987 0.8674
6.000 0.5483 0.00948 0.00461 0.0215 0.3391 0.8706
6.250 0.5487 0.01023 0.00512 0.0260 0.2867 0.8731
6.500 0.5540 0.01084 0.00557 0.0294 0.2428 0.8757
6.750 0.5615 0.01148 0.00605 0.0325 0.2029 0.8780
7.000 0.5718 0.01205 0.00650 0.0350 0.1696 0.8804
7.250 0.5825 0.01265 0.00696 0.0373 0.1372 0.8830
7.500 0.5957 0.01318 0.00739 0.0392 0.1133 0.8853
7.750 0.6093 0.01372 0.00781 0.0410 0.0920 0.8873
8.000 0.6243 0.01417 0.00823 0.0425 0.0754 0.8896
8.250 0.6402 0.01462 0.00865 0.0439 0.0635 0.8917
8.500 0.6558 0.01511 0.00909 0.0453 0.0514 0.8939
8.750 0.6712 0.01561 0.00954 0.0467 0.0406 0.8963
9.000 0.6877 0.01608 0.00998 0.0479 0.0345 0.8988
9.250 0.7051 0.01652 0.01042 0.0490 0.0291 0.9010
9.500 0.7219 0.01696 0.01087 0.0501 0.0259 0.9035
9.750 0.7375 0.01748 0.01141 0.0514 0.0215 0.9059
10.000 0.7556 0.01788 0.01186 0.0523 0.0201 0.9083
10.250 0.7717 0.01840 0.01235 0.0534 0.0168 0.9110
10.500 0.7873 0.01896 0.01294 0.0546 0.0142 0.9136
10.750 0.8045 0.01944 0.01346 0.0556 0.0133 0.9161
11.000 0.8206 0.01993 0.01398 0.0566 0.0115 0.9192
11.250 0.8344 0.02058 0.01464 0.0580 0.0091 0.9224
11.500 0.8504 0.02113 0.01524 0.0590 0.0081 0.9257
11.750 0.8626 0.02195 0.01606 0.0605 0.0061 0.9288
12.000 0.8769 0.02259 0.01678 0.0617 0.0048 0.9324
12.250 0.8860 0.02359 0.01784 0.0636 0.0034 0.9364
12.500 0.9002 0.02427 0.01857 0.0646 0.0029 0.9405
12.750 0.9122 0.02513 0.01953 0.0660 0.0031 0.9449
13.000 0.9232 0.02604 0.02055 0.0674 0.0031 0.9501
13.250 0.9368 0.02679 0.02135 0.0684 0.0026 0.9559
13.500 0.9431 0.02839 0.02309 0.0698 0.0020 0.9623
13.750 0.9516 0.03003 0.02488 0.0705 0.0019 0.9690
14.000 0.9651 0.03176 0.02675 0.0700 0.0019 0.9740
14.250 0.9957 0.03210 0.02708 0.0678 0.0021 0.9779
14.500 0.9889 0.03583 0.03111 0.0684 0.0018 0.9828
14.750 1.0071 0.03738 0.03277 0.0670 0.0018 0.9868
15.000 1.0147 0.03983 0.03537 0.0662 0.0018 0.9928
15.250 1.0153 0.04218 0.03785 0.0671 0.0018 1.0000
15.500 1.0162 0.04428 0.04004 0.0680 0.0018 1.0000
15.750 1.0141 0.04678 0.04266 0.0689 0.0017 1.0000
16.000 1.0115 0.04945 0.04545 0.0695 0.0018 1.0000
16.250 1.0046 0.05274 0.04888 0.0700 0.0018 1.0000
16.500 0.9964 0.05635 0.05264 0.0701 0.0017 1.0000
16.750 0.9823 0.06092 0.05740 0.0698 0.0017 1.0000
17.000 0.9806 0.06415 0.06071 0.0690 0.0018 1.0000
17.250 0.9628 0.06980 0.06654 0.0677 0.0017 1.0000
17.500 0.9509 0.07495 0.07183 0.0658 0.0017 1.0000
17.750 0.9307 0.08182 0.07887 0.0630 0.0017 1.0000
18.000 0.9231 0.08696 0.08411 0.0605 0.0017 1.0000
18.250 0.8905 0.09688 0.09424 0.0557 0.0017 1.0000
18.500 0.8654 0.10603 0.10356 0.0509 0.0018 1.0000
18.750 0.8426 0.11512 0.11277 0.0461 0.0018 1.0000
19.000 0.8114 0.12612 0.12392 0.0405 0.0018 1.0000
19.250 0.7845 0.13672 0.13465 0.0352 0.0019 1.0000
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