NREL's S834 Airfoil (s834-nr) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S834 Airfoil (s834-nr) Reynolds number: 50,000 Max Cl/Cd: 29.85 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s834-nr-50000.txt Download as CSV file: xf-s834-nr-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5301 0.11104 0.10393 -0.0465 1.0000 0.1887
-11.250 -0.5379 0.10623 0.09917 -0.0465 1.0000 0.1896
-11.000 -0.7108 0.07960 0.07295 -0.0615 1.0000 0.1463
-10.750 -0.7401 0.07562 0.06899 -0.0591 1.0000 0.1456
-10.500 -0.7713 0.07236 0.06573 -0.0553 1.0000 0.1446
-10.250 -0.8035 0.06935 0.06270 -0.0506 1.0000 0.1434
-10.000 -0.8351 0.06591 0.05920 -0.0460 1.0000 0.1425
-9.750 -0.8631 0.06247 0.05557 -0.0413 1.0000 0.1427
-9.500 -0.8873 0.05905 0.05187 -0.0366 1.0000 0.1437
-9.250 -0.9096 0.05559 0.04797 -0.0318 1.0000 0.1456
-9.000 -0.8974 0.05381 0.04627 -0.0298 1.0000 0.1542
-8.750 -0.9086 0.05044 0.04244 -0.0257 1.0000 0.1582
-8.500 -0.9045 0.04780 0.03964 -0.0230 1.0000 0.1650
-8.250 -0.9063 0.04534 0.03669 -0.0195 1.0000 0.1742
-8.000 -0.8944 0.04365 0.03501 -0.0174 1.0000 0.1866
-7.750 -0.8828 0.04172 0.03298 -0.0152 1.0000 0.1985
-7.500 -0.8727 0.04009 0.03121 -0.0128 1.0000 0.2144
-7.250 -0.8615 0.03841 0.02932 -0.0106 1.0000 0.2307
-7.000 -0.8465 0.03700 0.02792 -0.0087 1.0000 0.2487
-6.750 -0.8318 0.03594 0.02690 -0.0067 1.0000 0.2700
-6.500 -0.8172 0.03471 0.02560 -0.0047 1.0000 0.2924
-6.250 -0.8024 0.03371 0.02452 -0.0027 1.0000 0.3172
-6.000 -0.7858 0.03288 0.02380 -0.0008 1.0000 0.3425
-5.750 -0.7697 0.03209 0.02307 0.0012 1.0000 0.3699
-5.500 -0.7533 0.03137 0.02240 0.0032 1.0000 0.3985
-5.250 -0.7370 0.03076 0.02184 0.0053 1.0000 0.4288
-5.000 -0.7205 0.03020 0.02134 0.0074 1.0000 0.4604
-4.750 -0.7043 0.02968 0.02084 0.0096 1.0000 0.4936
-4.500 -0.6876 0.02939 0.02064 0.0121 1.0000 0.5257
-4.250 -0.6714 0.02918 0.02053 0.0147 1.0000 0.5588
-4.000 -0.6558 0.02900 0.02040 0.0174 1.0000 0.5936
-3.750 -0.6405 0.02902 0.02050 0.0206 1.0000 0.6272
-3.500 -0.6257 0.02921 0.02076 0.0241 1.0000 0.6600
-3.250 -0.6115 0.02949 0.02107 0.0277 1.0000 0.6929
-3.000 -0.5982 0.02981 0.02136 0.0315 1.0000 0.7268
-2.750 -0.5833 0.03044 0.02197 0.0354 1.0000 0.7575
-2.500 -0.5663 0.03121 0.02270 0.0391 1.0000 0.7883
-2.250 -0.5438 0.03212 0.02351 0.0417 1.0000 0.8197
-2.000 -0.5144 0.03304 0.02427 0.0425 1.0000 0.8532
-1.750 -0.4683 0.03413 0.02516 0.0399 1.0000 0.8869
-1.500 -0.3845 0.03567 0.02639 0.0298 1.0000 0.9172
-1.250 -0.2869 0.03685 0.02724 0.0160 1.0000 0.9459
-1.000 -0.1916 0.03753 0.02765 0.0014 1.0000 0.9747
-0.750 -0.1038 0.03787 0.02775 -0.0129 1.0000 1.0000
-0.500 -0.1102 0.03716 0.02698 -0.0101 1.0000 1.0000
-0.250 -0.1161 0.03652 0.02629 -0.0072 1.0000 1.0000
0.000 -0.1211 0.03597 0.02567 -0.0043 1.0000 1.0000
0.250 -0.1250 0.03550 0.02514 -0.0013 1.0000 1.0000
0.500 -0.1275 0.03511 0.02469 0.0017 1.0000 1.0000
0.750 -0.1286 0.03480 0.02432 0.0045 1.0000 1.0000
1.000 -0.1284 0.03458 0.02403 0.0073 1.0000 1.0000
1.250 -0.1267 0.03443 0.02382 0.0099 1.0000 1.0000
1.500 -0.1237 0.03436 0.02370 0.0123 1.0000 1.0000
1.750 -0.1192 0.03438 0.02367 0.0145 1.0000 1.0000
2.000 -0.1135 0.03449 0.02372 0.0165 1.0000 1.0000
2.250 -0.1063 0.03469 0.02387 0.0183 1.0000 1.0000
2.500 -0.0974 0.03500 0.02414 0.0197 1.0000 1.0000
2.750 -0.0869 0.03543 0.02453 0.0208 1.0000 1.0000
3.000 -0.0753 0.03596 0.02504 0.0216 1.0000 1.0000
3.250 -0.0628 0.03659 0.02565 0.0222 1.0000 1.0000
3.500 -0.0498 0.03731 0.02636 0.0227 1.0000 1.0000
3.750 -0.0364 0.03812 0.02717 0.0230 1.0000 1.0000
4.000 -0.0229 0.03902 0.02807 0.0231 1.0000 1.0000
4.250 0.1395 0.04498 0.03423 -0.0018 0.9022 1.0000
4.500 0.1702 0.04582 0.03513 -0.0036 0.8795 1.0000
4.750 0.2123 0.04700 0.03641 -0.0069 0.8579 1.0000
5.000 0.2413 0.04777 0.03727 -0.0081 0.8366 1.0000
5.250 0.2855 0.04876 0.03837 -0.0113 0.8162 1.0000
5.500 0.3095 0.04939 0.03912 -0.0115 0.7948 1.0000
5.750 0.3579 0.05003 0.03992 -0.0147 0.7747 1.0000
6.000 0.3785 0.05056 0.04056 -0.0142 0.7523 1.0000
6.250 0.4287 0.05066 0.04089 -0.0168 0.7320 1.0000
6.500 0.4497 0.05106 0.04142 -0.0160 0.7088 1.0000
6.750 0.5060 0.05029 0.04091 -0.0183 0.6884 1.0000
7.000 0.5296 0.05029 0.04108 -0.0172 0.6638 1.0000
7.250 0.5694 0.04943 0.04048 -0.0171 0.6405 1.0000
7.500 0.6355 0.04640 0.03783 -0.0180 0.6183 1.0000
7.750 0.6843 0.04360 0.03535 -0.0168 0.5929 1.0000
8.000 0.8171 0.03431 0.02671 -0.0205 0.5555 1.0000
8.250 0.8912 0.03049 0.02283 -0.0215 0.4852 1.0000
8.500 0.9097 0.03048 0.02245 -0.0181 0.4245 1.0000
8.750 0.9230 0.03139 0.02295 -0.0148 0.3677 1.0000
9.000 0.9312 0.03278 0.02399 -0.0113 0.3193 1.0000
9.250 0.9404 0.03439 0.02526 -0.0083 0.2760 1.0000
9.500 0.9541 0.03625 0.02682 -0.0061 0.2371 1.0000
9.750 0.9695 0.03831 0.02872 -0.0043 0.2045 1.0000
10.000 0.9861 0.04050 0.03079 -0.0028 0.1778 1.0000
10.250 1.0125 0.04325 0.03340 -0.0028 0.1542 1.0000
10.500 1.0246 0.04567 0.03595 -0.0008 0.1391 1.0000
10.750 1.0445 0.04883 0.03923 -0.0001 0.1265 1.0000
11.000 1.0523 0.05120 0.04184 0.0023 0.1173 1.0000
11.250 1.0527 0.05444 0.04541 0.0054 0.1120 1.0000
11.500 1.0448 0.05755 0.04893 0.0094 0.1094 1.0000
11.750 1.0388 0.06065 0.05229 0.0126 0.1063 1.0000
12.000 1.0506 0.06431 0.05593 0.0134 0.1007 1.0000
12.250 1.0288 0.06736 0.05931 0.0175 0.1001 1.0000
12.500 1.0059 0.07088 0.06314 0.0209 0.0998 1.0000
12.750 0.9811 0.07476 0.06728 0.0234 0.0996 1.0000
13.000 0.9567 0.07918 0.07192 0.0249 0.0999 1.0000
13.250 0.9336 0.08411 0.07703 0.0254 0.1004 1.0000
13.500 0.9084 0.08960 0.08267 0.0250 0.1009 1.0000
13.750 0.8878 0.09554 0.08872 0.0239 0.1015 1.0000
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Polar data table (+)
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