NREL's S815 Airfoil (s815-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S815 Airfoil (s815-nr) Reynolds number: 100,000 Max Cl/Cd: 35.97 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s815-nr-100000-n5.txt Download as CSV file: xf-s815-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S815 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1107 0.11892 0.11102 -0.0421 0.9791 0.2885
-8.250 -0.0947 0.11617 0.10825 -0.0448 0.9729 0.2899
-8.000 -0.0900 0.11309 0.10512 -0.0483 0.9672 0.2942
-7.750 -0.0565 0.11128 0.10334 -0.0506 0.9614 0.2954
-7.500 -0.0287 0.10947 0.10156 -0.0526 0.9534 0.2968
-7.250 -0.0077 0.10740 0.09951 -0.0542 0.9445 0.2979
-7.000 0.0120 0.10512 0.09723 -0.0562 0.9352 0.2986
-6.750 0.0243 0.10321 0.09535 -0.0564 0.9202 0.2994
-6.500 0.0364 0.10129 0.09344 -0.0567 0.9040 0.3001
-6.000 0.0685 0.09715 0.08930 -0.0590 0.8743 0.3025
-5.750 0.0875 0.09472 0.08684 -0.0616 0.8614 0.3049
-5.500 0.1094 0.09180 0.08385 -0.0654 0.8496 0.3062
-5.250 0.1319 0.08877 0.08073 -0.0695 0.8350 0.3070
-5.000 0.1512 0.08534 0.07718 -0.0748 0.8201 0.3081
-4.750 0.1902 0.08226 0.07398 -0.0816 0.8034 0.3096
-4.500 0.2473 0.08009 0.07169 -0.0882 0.7829 0.3108
-4.250 0.2904 0.07817 0.06963 -0.0932 0.7611 0.3120
-4.000 0.3231 0.07654 0.06786 -0.0966 0.7403 0.3132
-3.750 0.3463 0.07491 0.06611 -0.0987 0.7216 0.3138
-3.500 0.3649 0.07333 0.06443 -0.1002 0.7051 0.3141
-3.250 0.3826 0.07184 0.06285 -0.1014 0.6906 0.3145
-3.000 0.3986 0.07045 0.06137 -0.1022 0.6772 0.3150
-2.750 0.4116 0.06916 0.06003 -0.1023 0.6648 0.3155
-2.500 0.4253 0.06785 0.05863 -0.1027 0.6541 0.3161
-2.250 0.4366 0.06672 0.05749 -0.1024 0.6434 0.3173
-2.000 0.4477 0.06553 0.05623 -0.1023 0.6347 0.3187
-1.750 0.4536 0.06427 0.05497 -0.1016 0.6258 0.3200
-1.500 0.4609 0.06285 0.05350 -0.1013 0.6185 0.3205
-1.250 0.4661 0.06136 0.05199 -0.1007 0.6119 0.3212
1.250 0.3738 0.03690 0.02726 -0.0913 0.5636 0.3414
1.500 0.3981 0.03689 0.02728 -0.0908 0.5592 0.3421
1.750 0.4225 0.03677 0.02718 -0.0908 0.5556 0.3428
2.000 0.4400 0.03661 0.02712 -0.0898 0.5511 0.3438
2.250 0.4592 0.03622 0.02680 -0.0896 0.5470 0.3452
2.500 0.4804 0.03547 0.02608 -0.0904 0.5434 0.3471
2.750 0.5047 0.03380 0.02431 -0.0936 0.5401 0.3502
3.250 0.5709 0.02956 0.01964 -0.1050 0.5326 0.3585
3.500 0.5936 0.02962 0.01983 -0.1044 0.5286 0.3595
3.750 0.6190 0.02969 0.02000 -0.1043 0.5252 0.3607
4.000 0.6467 0.02973 0.02011 -0.1046 0.5222 0.3620
4.250 0.6767 0.02975 0.02017 -0.1054 0.5195 0.3636
4.500 0.7073 0.02976 0.02021 -0.1064 0.5167 0.3655
4.750 0.7283 0.02978 0.02036 -0.1060 0.5127 0.3678
5.000 0.7548 0.02969 0.02033 -0.1068 0.5090 0.3708
5.250 0.7882 0.02944 0.02001 -0.1091 0.5056 0.3746
5.500 0.8170 0.02950 0.02015 -0.1096 0.5023 0.3766
5.750 0.8470 0.02966 0.02039 -0.1100 0.4993 0.3782
6.000 0.8692 0.02993 0.02081 -0.1093 0.4956 0.3799
6.250 0.8859 0.03023 0.02129 -0.1078 0.4910 0.3817
6.500 0.9089 0.03043 0.02160 -0.1074 0.4867 0.3840
6.750 0.9389 0.03048 0.02169 -0.1081 0.4828 0.3868
7.000 0.9775 0.03039 0.02153 -0.1103 0.4791 0.3905
7.250 0.9932 0.03066 0.02192 -0.1090 0.4737 0.3934
7.500 1.0080 0.03096 0.02242 -0.1070 0.4681 0.3951
7.750 1.0346 0.03102 0.02257 -0.1067 0.4629 0.3974
8.000 1.0607 0.03111 0.02274 -0.1063 0.4574 0.4002
8.250 1.0657 0.03154 0.02338 -0.1030 0.4506 0.4028
8.500 1.0914 0.03146 0.02331 -0.1027 0.4439 0.4067
8.750 1.1127 0.03148 0.02333 -0.1019 0.4372 0.4109
9.000 1.1149 0.03189 0.02394 -0.0981 0.4298 0.4130
9.250 1.1411 0.03172 0.02382 -0.0975 0.4225 0.4158
9.500 1.1407 0.03244 0.02476 -0.0937 0.4148 0.4180
9.750 1.1542 0.03271 0.02512 -0.0917 0.4065 0.4211
10.000 1.1642 0.03317 0.02567 -0.0895 0.3984 0.4243
10.250 1.1693 0.03386 0.02646 -0.0869 0.3890 0.4277
10.500 1.1765 0.03453 0.02722 -0.0847 0.3796 0.4308
10.750 1.1768 0.03552 0.02839 -0.0818 0.3692 0.4329
11.000 1.1719 0.03702 0.03008 -0.0789 0.3581 0.4350
11.250 1.1718 0.03834 0.03151 -0.0767 0.3460 0.4379
11.500 1.1652 0.04032 0.03360 -0.0745 0.3322 0.4406
11.750 1.1555 0.04287 0.03624 -0.0727 0.3169 0.4433
12.000 1.1505 0.04530 0.03866 -0.0716 0.2994 0.4467
12.250 1.1484 0.04761 0.04089 -0.0707 0.2805 0.4498
12.500 1.1418 0.05044 0.04369 -0.0698 0.2618 0.4519
12.750 1.1328 0.05377 0.04698 -0.0693 0.2441 0.4541
13.000 1.1235 0.05738 0.05055 -0.0691 0.2273 0.4564
13.250 1.1148 0.06112 0.05425 -0.0691 0.2115 0.4590
13.500 1.1072 0.06494 0.05803 -0.0695 0.1965 0.4617
13.750 1.1011 0.06878 0.06184 -0.0701 0.1824 0.4647
14.000 1.0969 0.07257 0.06557 -0.0708 0.1693 0.4681
14.250 1.0931 0.07625 0.06928 -0.0714 0.1576 0.4704
14.500 1.0898 0.07993 0.07296 -0.0721 0.1469 0.4731
14.750 1.0883 0.08354 0.07659 -0.0729 0.1366 0.4762
15.000 1.0884 0.08706 0.08013 -0.0738 0.1273 0.4798
15.250 1.0885 0.09063 0.08365 -0.0749 0.1191 0.4838
15.500 1.0904 0.09411 0.08715 -0.0760 0.1110 0.4879
15.750 1.0921 0.09746 0.09055 -0.0770 0.1040 0.4909
16.000 1.0936 0.10092 0.09405 -0.0781 0.0977 0.4945
16.250 1.0971 0.10419 0.09737 -0.0792 0.0917 0.4988
16.500 1.0996 0.10765 0.10083 -0.0805 0.0864 0.5035
16.750 1.1040 0.11088 0.10410 -0.0818 0.0814 0.5080
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Polar data table (+)
Polar graphs
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