NREL's S834 Airfoil (s834-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S834 Airfoil (s834-nr) Reynolds number: 100,000 Max Cl/Cd: 44.67 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s834-nr-100000-n5.txt Download as CSV file: xf-s834-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S834 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.5925 0.11878 0.11351 -0.0567 1.0000 0.0305
-15.250 -0.6400 0.10458 0.09921 -0.0633 1.0000 0.0294
-15.000 -0.6752 0.09428 0.08883 -0.0682 1.0000 0.0285
-14.750 -0.7044 0.08593 0.08033 -0.0721 1.0000 0.0280
-14.500 -0.7290 0.07904 0.07327 -0.0750 1.0000 0.0279
-14.250 -0.7489 0.07342 0.06750 -0.0770 1.0000 0.0281
-14.000 -0.7675 0.06846 0.06239 -0.0784 1.0000 0.0285
-13.750 -0.7831 0.06421 0.05797 -0.0791 1.0000 0.0288
-13.500 -0.7987 0.06035 0.05394 -0.0793 1.0000 0.0297
-13.250 -0.8119 0.05700 0.05041 -0.0788 1.0000 0.0303
-13.000 -0.8248 0.05396 0.04717 -0.0779 1.0000 0.0312
-12.750 -0.8360 0.05129 0.04434 -0.0764 1.0000 0.0320
-12.500 -0.8462 0.04894 0.04196 -0.0745 1.0000 0.0330
-12.250 -0.8566 0.04687 0.03984 -0.0722 1.0000 0.0339
-12.000 -0.8664 0.04504 0.03789 -0.0695 1.0000 0.0350
-11.750 -0.8759 0.04338 0.03615 -0.0665 1.0000 0.0361
-11.500 -0.8851 0.04182 0.03448 -0.0630 1.0000 0.0373
-11.250 -0.8943 0.04044 0.03298 -0.0592 1.0000 0.0389
-11.000 -0.9032 0.03924 0.03162 -0.0551 1.0000 0.0408
-10.750 -0.9124 0.03811 0.03036 -0.0507 1.0000 0.0423
-10.500 -0.9268 0.03702 0.02926 -0.0454 1.0000 0.0436
-10.250 -0.9312 0.03600 0.02819 -0.0416 0.9986 0.0457
-10.000 -0.9148 0.03474 0.02677 -0.0416 0.9945 0.0501
-9.750 -0.8993 0.03344 0.02532 -0.0411 0.9905 0.0549
-9.500 -0.8831 0.03234 0.02416 -0.0408 0.9861 0.0604
-9.250 -0.8621 0.03127 0.02294 -0.0410 0.9826 0.0672
-9.000 -0.8470 0.03031 0.02192 -0.0401 0.9779 0.0744
-8.750 -0.8283 0.02935 0.02086 -0.0397 0.9736 0.0825
-8.500 -0.8044 0.02853 0.01992 -0.0401 0.9703 0.0926
-8.250 -0.7882 0.02775 0.01911 -0.0390 0.9655 0.1031
-8.000 -0.7686 0.02701 0.01834 -0.0385 0.9611 0.1148
-7.750 -0.7437 0.02634 0.01763 -0.0389 0.9578 0.1294
-7.500 -0.7243 0.02573 0.01699 -0.0381 0.9534 0.1441
-7.250 -0.7050 0.02516 0.01640 -0.0373 0.9486 0.1589
-7.000 -0.6801 0.02461 0.01582 -0.0375 0.9451 0.1771
-6.750 -0.6536 0.02411 0.01532 -0.0381 0.9420 0.1971
-6.500 -0.6383 0.02367 0.01488 -0.0362 0.9361 0.2153
-6.250 -0.6135 0.02323 0.01445 -0.0363 0.9323 0.2360
-6.000 -0.5844 0.02284 0.01405 -0.0372 0.9295 0.2605
-5.750 -0.5679 0.02248 0.01373 -0.0355 0.9238 0.2798
-5.500 -0.5436 0.02215 0.01337 -0.0353 0.9195 0.3044
-5.250 -0.5148 0.02181 0.01307 -0.0359 0.9165 0.3298
-5.000 -0.4943 0.02153 0.01283 -0.0349 0.9115 0.3534
-4.750 -0.4715 0.02128 0.01259 -0.0343 0.9067 0.3782
-4.250 -0.4167 0.02079 0.01217 -0.0348 0.8997 0.4326
-4.000 -0.3975 0.02062 0.01206 -0.0334 0.8939 0.4572
-3.750 -0.3688 0.02042 0.01190 -0.0338 0.8905 0.4854
-3.500 -0.3373 0.02023 0.01176 -0.0346 0.8880 0.5145
-3.250 -0.3215 0.02017 0.01174 -0.0325 0.8811 0.5389
-3.000 -0.2937 0.02004 0.01167 -0.0325 0.8773 0.5671
-2.750 -0.2624 0.01992 0.01160 -0.0332 0.8747 0.5955
-2.500 -0.2442 0.01994 0.01170 -0.0313 0.8685 0.6204
-2.250 -0.2179 0.01992 0.01172 -0.0309 0.8641 0.6464
-2.000 -0.1870 0.01989 0.01173 -0.0313 0.8613 0.6726
-1.750 -0.1657 0.01998 0.01186 -0.0300 0.8558 0.6964
-1.500 -0.1421 0.02009 0.01200 -0.0289 0.8507 0.7184
-1.250 -0.1116 0.02012 0.01203 -0.0292 0.8476 0.7410
-1.000 -0.0859 0.02025 0.01219 -0.0285 0.8433 0.7599
-0.750 -0.0666 0.02046 0.01241 -0.0266 0.8367 0.7785
-0.500 -0.0362 0.02052 0.01246 -0.0268 0.8336 0.7961
0.000 0.0082 0.02087 0.01279 -0.0242 0.8222 0.8283
0.250 0.0391 0.02089 0.01280 -0.0245 0.8191 0.8427
0.750 0.0829 0.02115 0.01306 -0.0219 0.8072 0.8710
1.000 0.1173 0.02111 0.01302 -0.0227 0.8045 0.8817
1.500 0.1686 0.02126 0.01320 -0.0217 0.7924 0.9048
1.750 0.2058 0.02106 0.01300 -0.0231 0.7897 0.9147
2.000 0.2292 0.02125 0.01322 -0.0225 0.7811 0.9255
2.250 0.2722 0.02108 0.01309 -0.0252 0.7775 0.9322
2.500 0.3185 0.02077 0.01282 -0.0284 0.7749 0.9387
2.750 0.3478 0.02091 0.01302 -0.0290 0.7654 0.9470
3.000 0.3966 0.02054 0.01272 -0.0327 0.7616 0.9522
3.250 0.4319 0.02053 0.01278 -0.0344 0.7524 0.9588
3.500 0.4855 0.02010 0.01244 -0.0391 0.7473 0.9616
3.750 0.5188 0.02001 0.01244 -0.0403 0.7366 0.9689
4.000 0.5667 0.01970 0.01222 -0.0441 0.7273 0.9720
4.250 0.6172 0.01927 0.01190 -0.0482 0.7174 0.9748
4.500 0.6538 0.01907 0.01180 -0.0499 0.7035 0.9806
4.750 0.6929 0.01886 0.01169 -0.0521 0.6871 0.9851
5.000 0.7278 0.01873 0.01165 -0.0536 0.6678 0.9908
5.250 0.7688 0.01848 0.01149 -0.0560 0.6463 0.9948
5.500 0.8049 0.01837 0.01142 -0.0576 0.6188 0.9998
5.750 0.8137 0.01836 0.01139 -0.0539 0.5937 1.0000
6.000 0.8205 0.01837 0.01135 -0.0498 0.5657 1.0000
6.250 0.8240 0.01845 0.01134 -0.0451 0.5352 1.0000
6.500 0.8255 0.01858 0.01139 -0.0401 0.5022 1.0000
6.750 0.8246 0.01880 0.01146 -0.0348 0.4670 1.0000
7.000 0.8231 0.01911 0.01159 -0.0295 0.4316 1.0000
7.250 0.8222 0.01953 0.01183 -0.0244 0.3968 1.0000
7.500 0.8241 0.02009 0.01220 -0.0201 0.3608 1.0000
7.750 0.8285 0.02076 0.01269 -0.0165 0.3260 1.0000
8.000 0.8349 0.02150 0.01328 -0.0134 0.2920 1.0000
8.250 0.8423 0.02231 0.01395 -0.0106 0.2598 1.0000
8.500 0.8508 0.02318 0.01469 -0.0081 0.2302 1.0000
8.750 0.8597 0.02410 0.01549 -0.0058 0.2016 1.0000
9.000 0.8696 0.02505 0.01639 -0.0037 0.1763 1.0000
9.250 0.8790 0.02607 0.01731 -0.0017 0.1523 1.0000
9.500 0.8888 0.02714 0.01830 0.0002 0.1314 1.0000
9.750 0.8983 0.02828 0.01937 0.0020 0.1130 1.0000
10.000 0.9083 0.02944 0.02049 0.0037 0.0967 1.0000
10.250 0.9173 0.03070 0.02172 0.0054 0.0833 1.0000
10.500 0.9256 0.03204 0.02304 0.0071 0.0722 1.0000
10.750 0.9327 0.03351 0.02449 0.0088 0.0633 1.0000
11.000 0.9419 0.03487 0.02595 0.0103 0.0557 1.0000
11.250 0.9466 0.03660 0.02769 0.0120 0.0500 1.0000
11.500 0.9548 0.03814 0.02938 0.0134 0.0450 1.0000
11.750 0.9597 0.03994 0.03121 0.0148 0.0408 1.0000
12.000 0.9655 0.04178 0.03315 0.0162 0.0372 1.0000
12.250 0.9724 0.04358 0.03510 0.0173 0.0342 1.0000
12.500 0.9768 0.04558 0.03718 0.0184 0.0316 1.0000
12.750 0.9785 0.04794 0.03956 0.0195 0.0293 1.0000
13.000 0.9852 0.04996 0.04181 0.0203 0.0270 1.0000
13.250 0.9899 0.05224 0.04425 0.0211 0.0254 1.0000
13.500 0.9929 0.05469 0.04683 0.0217 0.0241 1.0000
13.750 0.9944 0.05727 0.04951 0.0221 0.0230 1.0000
14.000 0.9933 0.06022 0.05253 0.0224 0.0219 1.0000
14.250 0.9925 0.06339 0.05591 0.0226 0.0207 1.0000
14.500 0.9913 0.06670 0.05946 0.0225 0.0200 1.0000
14.750 0.9871 0.07040 0.06344 0.0221 0.0191 1.0000
15.000 0.9808 0.07450 0.06777 0.0212 0.0183 1.0000
15.250 0.9737 0.07892 0.07239 0.0201 0.0180 1.0000
15.500 0.9643 0.08382 0.07751 0.0185 0.0178 1.0000
15.750 0.9527 0.08931 0.08322 0.0164 0.0176 1.0000
16.000 0.9390 0.09546 0.08959 0.0135 0.0175 1.0000
16.250 0.9219 0.10257 0.09691 0.0098 0.0174 1.0000
16.500 0.9024 0.11069 0.10526 0.0052 0.0176 1.0000
16.750 0.8768 0.12079 0.11559 -0.0009 0.0177 1.0000
17.000 0.8417 0.13431 0.12929 -0.0092 0.0183 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S834 Airfoil (s834-nr)