NREL's S835 Airfoil (s835-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S835 Airfoil (s835-nr) Reynolds number: 50,000 Max Cl/Cd: 19.2 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s835-nr-50000-n5.txt Download as CSV file: xf-s835-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S835 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4668 0.12756 0.11741 -0.0405 1.0000 0.2285
-11.750 -0.4806 0.12350 0.11334 -0.0408 1.0000 0.2335
-11.500 -0.4893 0.12014 0.10997 -0.0406 1.0000 0.2378
-11.250 -0.4780 0.11941 0.10925 -0.0392 1.0000 0.2403
-11.000 -0.4746 0.11773 0.10757 -0.0382 1.0000 0.2439
-10.750 -0.4885 0.11394 0.10378 -0.0380 1.0000 0.2491
-10.500 -0.5031 0.11012 0.09996 -0.0377 1.0000 0.2541
-10.250 -0.4915 0.10965 0.09948 -0.0360 1.0000 0.2567
-10.000 -0.4889 0.10809 0.09793 -0.0348 1.0000 0.2602
-9.500 -0.5226 0.10055 0.09040 -0.0335 1.0000 0.2712
-9.250 -0.5128 0.10010 0.08997 -0.0317 1.0000 0.2739
-8.750 -0.5667 0.09083 0.08070 -0.0302 1.0000 0.2871
-8.500 -0.5508 0.09122 0.08112 -0.0280 1.0000 0.2891
-8.250 -0.5428 0.09075 0.08066 -0.0261 1.0000 0.2920
-7.750 -0.6049 0.08148 0.07140 -0.0234 1.0000 0.3059
-7.500 -0.5775 0.08187 0.07178 -0.0233 0.9974 0.3084
-7.250 -0.5552 0.08086 0.07073 -0.0249 0.9928 0.3127
-6.500 -0.6504 0.06214 0.05177 -0.0298 0.9688 0.3424
-6.250 -0.6035 0.06373 0.05336 -0.0309 0.9657 0.3446
-6.000 -0.6914 0.05304 0.04238 -0.0315 0.9518 0.3601
-5.750 -0.6572 0.05414 0.04353 -0.0310 0.9473 0.3624
-5.500 -0.6292 0.05465 0.04406 -0.0305 0.9419 0.3655
-5.250 -0.6139 0.05316 0.04250 -0.0317 0.9365 0.3722
-5.000 -0.6280 0.04932 0.03847 -0.0314 0.9276 0.3811
-4.750 -0.5964 0.04985 0.03904 -0.0316 0.9230 0.3846
-4.500 -0.5769 0.04919 0.03833 -0.0317 0.9175 0.3902
-4.250 -0.5746 0.04635 0.03528 -0.0325 0.9099 0.3997
-4.000 -0.5417 0.04696 0.03595 -0.0328 0.9057 0.4033
-3.750 -0.5238 0.04666 0.03565 -0.0320 0.8994 0.4083
-3.500 -0.5105 0.04439 0.03314 -0.0338 0.8928 0.4185
-3.250 -0.4776 0.04497 0.03381 -0.0341 0.8888 0.4222
-3.000 -0.4607 0.04492 0.03380 -0.0328 0.8821 0.4270
-2.750 -0.4405 0.04350 0.03219 -0.0344 0.8759 0.4368
-2.500 -0.4091 0.04367 0.03241 -0.0351 0.8717 0.4415
-2.250 -0.3920 0.04376 0.03256 -0.0336 0.8649 0.4463
-2.000 -0.3693 0.04307 0.03177 -0.0345 0.8587 0.4548
-1.750 -0.3384 0.04288 0.03159 -0.0358 0.8542 0.4615
-1.500 -0.3196 0.04305 0.03182 -0.0345 0.8475 0.4664
-1.250 -0.2972 0.04262 0.03133 -0.0350 0.8409 0.4747
-1.000 -0.2662 0.04245 0.03117 -0.0362 0.8362 0.4819
-0.750 -0.2450 0.04268 0.03146 -0.0353 0.8297 0.4873
-0.500 -0.2238 0.04236 0.03110 -0.0356 0.8226 0.4959
-0.250 -0.1932 0.04231 0.03108 -0.0365 0.8177 0.5028
0.000 -0.1696 0.04254 0.03138 -0.0359 0.8116 0.5087
0.250 -0.1494 0.04229 0.03109 -0.0361 0.8037 0.5183
0.500 -0.1200 0.04242 0.03128 -0.0364 0.7986 0.5244
0.750 -0.0942 0.04261 0.03154 -0.0362 0.7929 0.5309
1.000 -0.0743 0.04240 0.03129 -0.0368 0.7843 0.5415
1.250 -0.0467 0.04269 0.03170 -0.0362 0.7789 0.5465
1.500 -0.0218 0.04286 0.03193 -0.0360 0.7726 0.5536
1.750 -0.0012 0.04284 0.03189 -0.0363 0.7638 0.5635
2.000 0.0275 0.04304 0.03222 -0.0359 0.7585 0.5692
2.250 0.0474 0.04329 0.03253 -0.0352 0.7505 0.5767
2.500 0.0720 0.04332 0.03259 -0.0358 0.7424 0.5860
2.750 0.1035 0.04338 0.03277 -0.0356 0.7374 0.5923
3.250 0.1471 0.04375 0.03325 -0.0352 0.7200 0.6089
3.500 0.1822 0.04359 0.03321 -0.0354 0.7157 0.6161
3.750 0.1908 0.04419 0.03386 -0.0339 0.7027 0.6248
4.000 0.2256 0.04394 0.03371 -0.0345 0.6972 0.6325
4.250 0.2357 0.04453 0.03441 -0.0324 0.6852 0.6392
4.500 0.2729 0.04424 0.03416 -0.0341 0.6785 0.6504
4.750 0.2872 0.04464 0.03470 -0.0320 0.6679 0.6561
5.000 0.3141 0.04457 0.03474 -0.0316 0.6593 0.6643
5.250 0.3576 0.04381 0.03407 -0.0332 0.6547 0.6745
5.500 0.3617 0.04467 0.03505 -0.0304 0.6396 0.6808
5.750 0.4049 0.04374 0.03423 -0.0316 0.6347 0.6911
6.000 0.4129 0.04452 0.03511 -0.0296 0.6192 0.6982
6.250 0.4530 0.04340 0.03412 -0.0295 0.6143 0.7074
6.500 0.4657 0.04411 0.03492 -0.0285 0.5983 0.7167
7.000 0.5171 0.04336 0.03442 -0.0264 0.5767 0.7341
7.250 0.5321 0.04361 0.03481 -0.0246 0.5622 0.7422
7.500 0.5735 0.04212 0.03344 -0.0245 0.5543 0.7523
7.750 0.5877 0.04247 0.03390 -0.0229 0.5377 0.7612
8.000 0.6063 0.04237 0.03393 -0.0211 0.5227 0.7705
8.250 0.6450 0.04100 0.03265 -0.0208 0.5109 0.7811
8.500 0.6657 0.04068 0.03244 -0.0191 0.4942 0.7908
8.750 0.6855 0.04059 0.03244 -0.0176 0.4756 0.8011
9.000 0.7049 0.04041 0.03232 -0.0159 0.4566 0.8117
9.250 0.7260 0.04016 0.03211 -0.0143 0.4362 0.8222
9.500 0.7475 0.03999 0.03193 -0.0129 0.4146 0.8340
9.750 0.7646 0.03991 0.03182 -0.0109 0.3926 0.8455
10.000 0.7762 0.04043 0.03232 -0.0089 0.3697 0.8577
10.250 0.7873 0.04107 0.03294 -0.0071 0.3469 0.8709
10.500 0.7958 0.04172 0.03356 -0.0050 0.3252 0.8852
10.750 0.8037 0.04249 0.03431 -0.0029 0.3043 0.9014
11.000 0.8114 0.04342 0.03521 -0.0013 0.2842 0.9202
11.250 0.8218 0.04451 0.03630 -0.0006 0.2640 0.9470
11.500 0.8310 0.04573 0.03747 -0.0004 0.2450 1.0000
11.750 0.8435 0.04754 0.03920 -0.0009 0.2264 1.0000
12.000 0.8550 0.04948 0.04106 -0.0014 0.2094 1.0000
12.250 0.8655 0.05154 0.04305 -0.0018 0.1937 1.0000
12.500 0.8755 0.05367 0.04513 -0.0022 0.1794 1.0000
12.750 0.8852 0.05586 0.04728 -0.0026 0.1665 1.0000
13.000 0.8945 0.05810 0.04945 -0.0030 0.1550 1.0000
13.250 0.9036 0.06033 0.05157 -0.0034 0.1447 1.0000
13.500 0.9112 0.06286 0.05418 -0.0038 0.1347 1.0000
13.750 0.9190 0.06541 0.05676 -0.0043 0.1260 1.0000
14.000 0.9273 0.06786 0.05917 -0.0047 0.1185 1.0000
14.250 0.9343 0.07049 0.06183 -0.0052 0.1115 1.0000
14.500 0.9401 0.07338 0.06482 -0.0058 0.1051 1.0000
14.750 0.9500 0.07566 0.06698 -0.0062 0.0999 1.0000
15.000 0.9516 0.07922 0.07078 -0.0071 0.0947 1.0000
15.250 0.9602 0.08170 0.07320 -0.0077 0.0904 1.0000
15.500 0.9587 0.08577 0.07753 -0.0088 0.0864 1.0000
15.750 0.9672 0.08828 0.07997 -0.0095 0.0829 1.0000
16.000 0.9600 0.09326 0.08524 -0.0113 0.0800 1.0000
16.250 0.9571 0.09762 0.08974 -0.0130 0.0772 1.0000
16.500 0.9647 0.10036 0.09243 -0.0140 0.0747 1.0000
16.750 0.9432 0.10795 0.10040 -0.0177 0.0730 1.0000
17.000 0.9197 0.11631 0.10906 -0.0223 0.0716 1.0000
17.250 0.8853 0.12741 0.12047 -0.0289 0.0707 1.0000
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