NREL's S829 Airfoil (s829-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S829 Airfoil (s829-nr) Reynolds number: 200,000 Max Cl/Cd: 35.63 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s829-nr-200000-n5.txt Download as CSV file: xf-s829-nr-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4867 0.08341 0.07981 -0.0764 0.9137 0.0080
-14.250 -0.5953 0.07608 0.07213 -0.0852 0.9579 0.0076
-14.000 -0.6101 0.06940 0.06526 -0.0899 0.9489 0.0075
-13.750 -0.6302 0.06317 0.05877 -0.0930 0.9402 0.0075
-13.500 -0.6464 0.05851 0.05387 -0.0941 0.9317 0.0075
-13.250 -0.6602 0.05473 0.04986 -0.0940 0.9241 0.0074
-13.000 -0.6781 0.05079 0.04560 -0.0928 0.9169 0.0075
-12.750 -0.6884 0.04782 0.04238 -0.0912 0.9104 0.0075
-12.500 -0.6957 0.04524 0.03954 -0.0893 0.9044 0.0075
-12.250 -0.7025 0.04260 0.03660 -0.0869 0.8994 0.0075
-12.000 -0.7062 0.04004 0.03377 -0.0846 0.8943 0.0076
-11.750 -0.7068 0.03760 0.03105 -0.0823 0.8902 0.0077
-11.500 -0.7031 0.03547 0.02866 -0.0803 0.8867 0.0079
-11.250 -0.6952 0.03370 0.02670 -0.0787 0.8828 0.0081
-11.000 -0.6851 0.03225 0.02508 -0.0771 0.8793 0.0084
-10.750 -0.6738 0.03091 0.02358 -0.0755 0.8761 0.0088
-10.500 -0.6602 0.02971 0.02216 -0.0741 0.8735 0.0089
-10.250 -0.6454 0.02849 0.02081 -0.0729 0.8701 0.0094
-10.000 -0.6302 0.02736 0.01953 -0.0716 0.8668 0.0103
-9.750 -0.6152 0.02628 0.01828 -0.0702 0.8640 0.0110
-9.500 -0.6003 0.02535 0.01720 -0.0688 0.8616 0.0115
-9.250 -0.5869 0.02433 0.01610 -0.0672 0.8594 0.0131
-9.000 -0.5678 0.02378 0.01551 -0.0665 0.8567 0.0164
-8.750 -0.5528 0.02291 0.01453 -0.0651 0.8540 0.0185
-8.500 -0.5370 0.02214 0.01373 -0.0637 0.8515 0.0221
-8.250 -0.5197 0.02153 0.01300 -0.0625 0.8493 0.0268
-8.000 -0.5031 0.02090 0.01236 -0.0612 0.8473 0.0339
-7.750 -0.4865 0.02029 0.01172 -0.0598 0.8453 0.0419
-7.500 -0.4687 0.01976 0.01117 -0.0587 0.8425 0.0511
-7.250 -0.4514 0.01924 0.01068 -0.0575 0.8401 0.0639
-7.000 -0.4342 0.01873 0.01021 -0.0562 0.8379 0.0799
-6.750 -0.4174 0.01823 0.00977 -0.0549 0.8359 0.1021
-6.500 -0.4020 0.01767 0.00934 -0.0533 0.8341 0.1324
-6.250 -0.3883 0.01708 0.00887 -0.0514 0.8324 0.1732
-6.000 -0.3760 0.01650 0.00850 -0.0493 0.8303 0.2212
-5.750 -0.3675 0.01588 0.00815 -0.0466 0.8276 0.2804
-5.500 -0.3644 0.01517 0.00776 -0.0427 0.8247 0.3505
-5.250 -0.3659 0.01445 0.00738 -0.0377 0.8220 0.4252
-5.000 -0.3717 0.01378 0.00713 -0.0315 0.8197 0.5133
-4.750 -0.2901 0.01499 0.00914 -0.0398 0.8206 0.6888
-4.500 -0.2672 0.01532 0.00940 -0.0385 0.8193 0.7178
-4.250 -0.2525 0.01534 0.00934 -0.0361 0.8179 0.7368
-4.000 -0.2372 0.01557 0.00952 -0.0338 0.8154 0.7512
-3.750 -0.2252 0.01579 0.00969 -0.0309 0.8129 0.7644
-3.500 -0.2182 0.01599 0.00983 -0.0269 0.8103 0.7769
-3.250 -0.1679 0.01688 0.01061 -0.0306 0.8097 0.7814
-3.000 -0.1539 0.01713 0.01080 -0.0278 0.8077 0.7920
-2.500 -0.0946 0.01800 0.01152 -0.0281 0.8057 0.8051
-2.250 -0.0532 0.01837 0.01181 -0.0307 0.8051 0.8067
-1.750 -0.0242 0.01859 0.01198 -0.0263 0.8007 0.8185
-1.500 0.0087 0.01879 0.01215 -0.0276 0.7989 0.8197
-1.250 0.0395 0.01895 0.01228 -0.0286 0.7974 0.8212
-0.750 0.0579 0.01890 0.01219 -0.0221 0.7932 0.8324
-0.500 0.0903 0.01895 0.01222 -0.0233 0.7922 0.8334
-0.250 0.1218 0.01898 0.01223 -0.0244 0.7912 0.8345
0.250 0.1375 0.01934 0.01263 -0.0177 0.7849 0.8437
0.500 0.1495 0.01939 0.01269 -0.0151 0.7820 0.8471
0.750 0.1767 0.01950 0.01280 -0.0154 0.7804 0.8484
1.000 0.2033 0.01952 0.01284 -0.0155 0.7790 0.8499
1.250 0.2293 0.01950 0.01284 -0.0155 0.7778 0.8516
1.500 0.2514 0.01942 0.01277 -0.0147 0.7766 0.8544
2.000 0.2498 0.01988 0.01331 -0.0047 0.7662 0.8631
2.250 0.2772 0.01983 0.01329 -0.0049 0.7647 0.8646
2.500 0.3042 0.01971 0.01322 -0.0050 0.7634 0.8662
3.000 0.3000 0.01992 0.01351 0.0057 0.7518 0.8756
3.250 0.3340 0.01970 0.01333 0.0044 0.7504 0.8763
3.500 0.3584 0.01955 0.01327 0.0049 0.7465 0.8778
3.750 0.3686 0.01942 0.01319 0.0082 0.7386 0.8809
4.000 0.4321 0.01820 0.01201 0.0022 0.7354 0.8795
4.250 0.4043 0.01818 0.01202 0.0126 0.7249 0.8876
4.500 0.4345 0.01762 0.01152 0.0125 0.7172 0.8884
4.750 0.4667 0.01699 0.01098 0.0120 0.7085 0.8892
5.000 0.4566 0.01715 0.01121 0.0191 0.6973 0.8934
5.250 0.4463 0.01723 0.01134 0.0260 0.6858 0.8994
5.500 0.4493 0.01734 0.01151 0.0303 0.6729 0.9029
5.750 0.4579 0.01757 0.01182 0.0333 0.6575 0.9056
6.000 0.4735 0.01748 0.01180 0.0354 0.6390 0.9085
6.250 0.4956 0.01704 0.01138 0.0368 0.6072 0.9112
6.500 0.5554 0.01559 0.00919 0.0332 0.4755 0.9093
6.750 0.5424 0.01625 0.00949 0.0400 0.4131 0.9153
7.000 0.5382 0.01719 0.01015 0.0448 0.3524 0.9187
7.250 0.5352 0.01812 0.01082 0.0492 0.2965 0.9229
7.500 0.5357 0.01887 0.01137 0.0529 0.2524 0.9279
7.750 0.5418 0.01972 0.01202 0.0556 0.2075 0.9312
8.000 0.5511 0.02055 0.01268 0.0575 0.1674 0.9342
8.250 0.5621 0.02127 0.01328 0.0593 0.1372 0.9376
8.500 0.5729 0.02191 0.01386 0.0612 0.1147 0.9415
8.750 0.5874 0.02262 0.01450 0.0623 0.0942 0.9443
9.000 0.6047 0.02335 0.01520 0.0629 0.0798 0.9470
9.250 0.6215 0.02406 0.01592 0.0636 0.0680 0.9501
9.500 0.6372 0.02474 0.01662 0.0645 0.0580 0.9538
9.750 0.6534 0.02549 0.01739 0.0652 0.0506 0.9570
10.000 0.6728 0.02636 0.01829 0.0651 0.0440 0.9591
10.250 0.6919 0.02722 0.01926 0.0651 0.0381 0.9615
10.500 0.7098 0.02813 0.02022 0.0652 0.0336 0.9643
10.750 0.7243 0.02920 0.02135 0.0659 0.0301 0.9680
11.000 0.7439 0.03014 0.02242 0.0656 0.0270 0.9706
11.250 0.7636 0.03124 0.02357 0.0651 0.0231 0.9726
11.500 0.7790 0.03267 0.02509 0.0651 0.0209 0.9751
11.750 0.7993 0.03361 0.02616 0.0647 0.0180 0.9777
12.000 0.8156 0.03479 0.02743 0.0645 0.0160 0.9808
12.250 0.8276 0.03655 0.02926 0.0646 0.0143 0.9833
12.500 0.8464 0.03785 0.03079 0.0640 0.0127 0.9852
12.750 0.8639 0.03916 0.03222 0.0633 0.0110 0.9875
13.000 0.8770 0.04081 0.03398 0.0629 0.0100 0.9905
13.250 0.8846 0.04300 0.03630 0.0630 0.0094 0.9942
13.500 0.8936 0.04538 0.03891 0.0631 0.0086 0.9992
13.750 0.8902 0.04702 0.04070 0.0656 0.0083 1.0000
14.000 0.8857 0.04871 0.04253 0.0681 0.0080 1.0000
14.250 0.8821 0.05084 0.04482 0.0700 0.0080 1.0000
14.500 0.8782 0.05328 0.04743 0.0714 0.0075 1.0000
14.750 0.8786 0.05528 0.04955 0.0720 0.0070 1.0000
15.000 0.8677 0.05912 0.05364 0.0729 0.0072 1.0000
15.250 0.8643 0.06190 0.05652 0.0729 0.0067 1.0000
15.500 0.8576 0.06541 0.06019 0.0726 0.0065 1.0000
15.750 0.8518 0.06895 0.06384 0.0719 0.0063 1.0000
16.000 0.8338 0.07470 0.06988 0.0708 0.0066 1.0000
16.250 0.8270 0.07894 0.07423 0.0690 0.0063 1.0000
16.500 0.8086 0.08547 0.08095 0.0663 0.0063 1.0000
16.750 0.7985 0.09099 0.08654 0.0630 0.0056 1.0000
17.000 0.7537 0.10420 0.10025 0.0570 0.0067 1.0000
17.250 0.7249 0.11530 0.11154 0.0508 0.0067 1.0000
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