NREL's S816 Airfoil (s816-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S816 Airfoil (s816-nr) Reynolds number: 100,000 Max Cl/Cd: 22.2 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s816-nr-100000-n5.txt Download as CSV file: xf-s816-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S816 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4359 0.10288 0.09792 -0.0735 1.0000 0.0216
-13.000 -0.4553 0.09769 0.09270 -0.0749 1.0000 0.0212
-12.750 -0.4749 0.09309 0.08806 -0.0758 1.0000 0.0208
-12.500 -0.4980 0.08853 0.08344 -0.0761 1.0000 0.0205
-12.250 -0.5208 0.08452 0.07937 -0.0757 1.0000 0.0202
-11.750 -0.5587 0.07169 0.06580 -0.0807 0.9783 0.0183
-11.500 -0.5563 0.06760 0.06153 -0.0831 0.9644 0.0182
-11.250 -0.5544 0.06345 0.05714 -0.0849 0.9465 0.0181
-11.000 -0.5481 0.05980 0.05326 -0.0864 0.9249 0.0180
-10.750 -0.5363 0.05611 0.04926 -0.0880 0.9031 0.0180
-10.500 -0.5176 0.05222 0.04500 -0.0897 0.8848 0.0180
-10.250 -0.4914 0.04862 0.04094 -0.0911 0.8680 0.0180
-10.000 -0.4548 0.04538 0.03723 -0.0920 0.8538 0.0182
-9.750 -0.4154 0.04310 0.03467 -0.0928 0.8394 0.0190
-9.500 -0.3844 0.04184 0.03321 -0.0932 0.8245 0.0199
-9.250 -0.3479 0.04089 0.03196 -0.0930 0.8118 0.0226
-9.000 -0.2923 0.04097 0.03181 -0.0923 0.8016 0.0247
-8.750 -0.2552 0.04115 0.03191 -0.0914 0.7917 0.0272
-8.500 -0.2065 0.04307 0.03379 -0.0898 0.7822 0.0328
-8.250 -0.1640 0.04537 0.03598 -0.0878 0.7737 0.0392
-8.000 -0.1414 0.04596 0.03663 -0.0864 0.7658 0.0453
-7.750 -0.1254 0.04568 0.03627 -0.0854 0.7592 0.0515
-7.500 -0.1152 0.04481 0.03538 -0.0846 0.7525 0.0578
-7.000 -0.1055 0.04207 0.03252 -0.0828 0.7413 0.0744
-6.750 -0.1079 0.04018 0.03061 -0.0817 0.7361 0.0822
-6.500 -0.1126 0.03807 0.02841 -0.0804 0.7318 0.0932
-6.250 -0.1226 0.03563 0.02599 -0.0789 0.7266 0.1055
-6.000 -0.1372 0.03287 0.02322 -0.0770 0.7219 0.1189
-5.750 -0.1560 0.02987 0.02020 -0.0748 0.7181 0.1373
-5.500 -0.1816 0.02685 0.01720 -0.0717 0.7140 0.1636
-5.250 -0.2090 0.02449 0.01484 -0.0676 0.7096 0.2005
-5.000 -0.2279 0.02318 0.01436 -0.0632 0.7058 0.4178
-4.750 -0.2121 0.02355 0.01454 -0.0621 0.7030 0.4578
-4.500 -0.1927 0.02416 0.01494 -0.0612 0.7002 0.4794
-4.250 -0.1662 0.02535 0.01606 -0.0604 0.6970 0.4939
-4.000 -0.1125 0.02877 0.01960 -0.0604 0.6944 0.5037
-3.750 -0.0962 0.02848 0.01915 -0.0597 0.6915 0.5105
-3.500 -0.0604 0.02955 0.02016 -0.0597 0.6892 0.5131
-3.250 -0.0406 0.02891 0.01935 -0.0597 0.6870 0.5145
-3.000 -0.0237 0.02817 0.01849 -0.0594 0.6844 0.5158
-2.750 -0.0068 0.02751 0.01772 -0.0591 0.6817 0.5173
-2.500 0.0117 0.02689 0.01697 -0.0590 0.6793 0.5192
-2.250 0.0309 0.02622 0.01614 -0.0592 0.6771 0.5215
-2.000 0.0519 0.02558 0.01532 -0.0596 0.6752 0.5238
-1.750 0.0774 0.02546 0.01512 -0.0598 0.6735 0.5246
-1.500 0.1035 0.02534 0.01494 -0.0602 0.6720 0.5255
-1.250 0.1288 0.02526 0.01480 -0.0604 0.6705 0.5264
-1.000 0.1499 0.02528 0.01482 -0.0600 0.6681 0.5275
-0.750 0.1719 0.02528 0.01482 -0.0598 0.6656 0.5288
-0.500 0.1950 0.02525 0.01478 -0.0597 0.6634 0.5303
-0.250 0.2190 0.02522 0.01471 -0.0599 0.6615 0.5319
0.000 0.2437 0.02517 0.01461 -0.0602 0.6599 0.5338
0.250 0.2691 0.02509 0.01447 -0.0607 0.6585 0.5359
0.500 0.2955 0.02499 0.01429 -0.0614 0.6573 0.5383
0.750 0.3222 0.02506 0.01437 -0.0618 0.6562 0.5397
1.000 0.3422 0.02536 0.01475 -0.0612 0.6543 0.5410
1.250 0.3593 0.02575 0.01524 -0.0602 0.6516 0.5426
1.500 0.3787 0.02607 0.01563 -0.0595 0.6491 0.5443
1.750 0.3999 0.02636 0.01597 -0.0591 0.6471 0.5465
2.000 0.4224 0.02662 0.01626 -0.0591 0.6455 0.5490
2.250 0.4465 0.02683 0.01647 -0.0593 0.6440 0.5520
2.500 0.4717 0.02703 0.01672 -0.0597 0.6427 0.5545
2.750 0.4981 0.02724 0.01701 -0.0599 0.6414 0.5564
3.000 0.5100 0.02796 0.01785 -0.0582 0.6385 0.5584
3.250 0.5105 0.02912 0.01915 -0.0551 0.6345 0.5604
3.500 0.5258 0.02974 0.01986 -0.0540 0.6315 0.5630
3.750 0.5477 0.03013 0.02030 -0.0539 0.6295 0.5660
4.000 0.5732 0.03041 0.02062 -0.0544 0.6278 0.5690
4.250 0.6004 0.03062 0.02097 -0.0548 0.6264 0.5711
5.250 0.5643 0.03787 0.02861 -0.0397 0.6013 0.5804
5.500 0.5895 0.03820 0.02901 -0.0401 0.5989 0.5842
5.750 0.6180 0.03827 0.02925 -0.0404 0.5973 0.5869
6.000 0.6504 0.03813 0.02927 -0.0411 0.5962 0.5904
6.500 0.6530 0.04158 0.03291 -0.0375 0.5819 0.5970
6.750 0.6796 0.04176 0.03324 -0.0377 0.5794 0.6007
7.250 0.7006 0.04389 0.03567 -0.0355 0.5666 0.6070
7.500 0.6911 0.04620 0.03808 -0.0331 0.5550 0.6103
7.750 0.7249 0.04576 0.03779 -0.0337 0.5525 0.6153
8.000 0.7569 0.04519 0.03747 -0.0338 0.5493 0.6193
8.500 0.7771 0.04609 0.03864 -0.0309 0.5256 0.6284
9.000 0.8461 0.04225 0.03523 -0.0297 0.5065 0.6390
10.000 0.8489 0.04840 0.04196 -0.0239 0.4339 0.6578
10.250 0.8718 0.04771 0.04141 -0.0230 0.4058 0.6638
10.500 0.9337 0.04206 0.03514 -0.0214 0.3074 0.6732
10.750 0.9265 0.04429 0.03695 -0.0192 0.2488 0.6781
11.000 0.9172 0.04708 0.03944 -0.0175 0.2027 0.6827
11.250 0.9123 0.04972 0.04184 -0.0163 0.1648 0.6885
11.500 0.9116 0.05207 0.04403 -0.0154 0.1353 0.6942
11.750 0.9145 0.05417 0.04603 -0.0146 0.1138 0.7005
12.000 0.9205 0.05607 0.04788 -0.0141 0.0971 0.7077
12.250 0.9268 0.05793 0.04978 -0.0134 0.0854 0.7148
12.500 0.9328 0.05991 0.05173 -0.0130 0.0762 0.7226
12.750 0.9417 0.06159 0.05355 -0.0125 0.0684 0.7308
13.000 0.9486 0.06351 0.05550 -0.0121 0.0624 0.7395
13.250 0.9581 0.06522 0.05735 -0.0117 0.0567 0.7494
13.500 0.9643 0.06719 0.05934 -0.0112 0.0523 0.7591
13.750 0.9754 0.06873 0.06108 -0.0108 0.0482 0.7709
14.000 0.9835 0.07059 0.06308 -0.0105 0.0446 0.7836
14.250 0.9914 0.07239 0.06495 -0.0099 0.0415 0.7980
14.500 1.0013 0.07398 0.06679 -0.0092 0.0384 0.8153
14.750 1.0079 0.07579 0.06877 -0.0086 0.0358 0.8372
15.000 1.0106 0.07765 0.07074 -0.0075 0.0338 0.8707
15.250 1.0143 0.07879 0.07212 -0.0061 0.0320 1.0000
15.500 1.0245 0.08112 0.07463 -0.0065 0.0297 1.0000
15.750 1.0308 0.08383 0.07743 -0.0072 0.0278 1.0000
16.000 1.0363 0.08658 0.08019 -0.0080 0.0263 1.0000
16.250 1.0429 0.08942 0.08319 -0.0084 0.0249 1.0000
16.500 1.0458 0.09284 0.08691 -0.0091 0.0236 1.0000
16.750 1.0458 0.09658 0.09087 -0.0102 0.0223 1.0000
17.000 1.0449 0.10039 0.09483 -0.0115 0.0213 1.0000
17.250 1.0440 0.10415 0.09866 -0.0131 0.0205 1.0000
17.500 1.0442 0.10777 0.10229 -0.0145 0.0197 1.0000
17.750 1.0344 0.11340 0.10826 -0.0168 0.0192 1.0000
18.000 1.0229 0.11946 0.11461 -0.0195 0.0188 1.0000
18.250 1.0081 0.12636 0.12180 -0.0229 0.0184 1.0000
18.500 0.9929 0.13360 0.12928 -0.0269 0.0183 1.0000
18.750 0.9742 0.14199 0.13791 -0.0319 0.0183 1.0000
19.000 0.9528 0.15153 0.14767 -0.0378 0.0184 1.0000
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