NREL's S834 Airfoil (s834-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S834 Airfoil (s834-nr) Reynolds number: 50,000 Max Cl/Cd: 26.63 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s834-nr-50000-n5.txt Download as CSV file: xf-s834-nr-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6164 0.09644 0.08918 -0.0673 1.0000 0.0655
-13.250 -0.6484 0.08796 0.08064 -0.0710 1.0000 0.0650
-13.000 -0.6788 0.08074 0.07333 -0.0738 1.0000 0.0646
-12.750 -0.7081 0.07464 0.06711 -0.0755 1.0000 0.0644
-12.500 -0.7345 0.06968 0.06201 -0.0759 1.0000 0.0644
-12.250 -0.7603 0.06543 0.05758 -0.0753 1.0000 0.0648
-12.000 -0.7835 0.06183 0.05377 -0.0736 1.0000 0.0652
-11.750 -0.7947 0.05945 0.05138 -0.0714 1.0000 0.0670
-11.500 -0.8035 0.05747 0.04938 -0.0689 1.0000 0.0689
-11.250 -0.8163 0.05540 0.04723 -0.0658 1.0000 0.0706
-11.000 -0.8302 0.05339 0.04508 -0.0621 1.0000 0.0724
-10.750 -0.8457 0.05156 0.04308 -0.0578 1.0000 0.0744
-10.500 -0.8618 0.04984 0.04113 -0.0529 1.0000 0.0768
-10.250 -0.8698 0.04820 0.03937 -0.0488 1.0000 0.0799
-10.000 -0.8728 0.04696 0.03816 -0.0453 1.0000 0.0837
-9.750 -0.8758 0.04536 0.03636 -0.0417 1.0000 0.0883
-9.500 -0.8742 0.04365 0.03445 -0.0385 1.0000 0.0930
-9.250 -0.8727 0.04245 0.03326 -0.0353 1.0000 0.0985
-9.000 -0.8706 0.04102 0.03159 -0.0321 1.0000 0.1059
-8.750 -0.8664 0.03988 0.03043 -0.0292 1.0000 0.1130
-8.500 -0.8597 0.03859 0.02899 -0.0265 1.0000 0.1212
-8.250 -0.8533 0.03747 0.02773 -0.0238 1.0000 0.1315
-8.000 -0.8460 0.03643 0.02672 -0.0212 1.0000 0.1417
-7.750 -0.8366 0.03539 0.02562 -0.0189 1.0000 0.1528
-7.500 -0.8269 0.03442 0.02460 -0.0165 1.0000 0.1661
-7.250 -0.8164 0.03353 0.02367 -0.0143 1.0000 0.1805
-7.000 -0.8049 0.03269 0.02279 -0.0122 1.0000 0.1962
-6.750 -0.7926 0.03191 0.02195 -0.0102 1.0000 0.2138
-6.500 -0.7795 0.03118 0.02118 -0.0084 1.0000 0.2326
-6.250 -0.7660 0.03052 0.02050 -0.0065 1.0000 0.2518
-6.000 -0.7453 0.02995 0.01988 -0.0061 0.9978 0.2758
-5.750 -0.7187 0.02955 0.01946 -0.0067 0.9936 0.3030
-5.500 -0.6933 0.02913 0.01906 -0.0070 0.9891 0.3303
-5.250 -0.6665 0.02884 0.01876 -0.0076 0.9845 0.3597
-5.000 -0.6404 0.02859 0.01847 -0.0079 0.9802 0.3895
-4.750 -0.6152 0.02834 0.01822 -0.0080 0.9752 0.4198
-4.500 -0.5873 0.02823 0.01814 -0.0084 0.9708 0.4513
-4.250 -0.5629 0.02807 0.01801 -0.0082 0.9659 0.4817
-4.000 -0.5374 0.02799 0.01796 -0.0080 0.9609 0.5130
-3.750 -0.5082 0.02806 0.01802 -0.0084 0.9567 0.5461
-3.500 -0.4863 0.02801 0.01800 -0.0074 0.9511 0.5763
-3.250 -0.4603 0.02812 0.01812 -0.0070 0.9461 0.6080
-3.000 -0.4323 0.02835 0.01836 -0.0070 0.9417 0.6396
-2.750 -0.4112 0.02847 0.01846 -0.0055 0.9357 0.6682
-2.500 -0.3835 0.02881 0.01880 -0.0052 0.9309 0.6976
-2.250 -0.3585 0.02916 0.01912 -0.0042 0.9257 0.7239
-2.000 -0.3338 0.02952 0.01945 -0.0033 0.9200 0.7491
-1.750 -0.3026 0.03001 0.01984 -0.0036 0.9157 0.7742
-1.500 -0.2818 0.03030 0.02008 -0.0021 0.9093 0.7977
-1.250 -0.2510 0.03079 0.02048 -0.0023 0.9043 0.8189
-1.000 -0.2232 0.03117 0.02076 -0.0023 0.8993 0.8415
-0.750 -0.1951 0.03153 0.02104 -0.0023 0.8932 0.8611
-0.500 -0.1579 0.03194 0.02136 -0.0042 0.8890 0.8804
-0.250 -0.1295 0.03220 0.02153 -0.0047 0.8829 0.8997
0.000 -0.0874 0.03256 0.02182 -0.0078 0.8780 0.9150
0.250 -0.0371 0.03293 0.02212 -0.0126 0.8746 0.9287
0.500 0.0055 0.03322 0.02236 -0.0163 0.8687 0.9420
0.750 0.0591 0.03351 0.02261 -0.0221 0.8641 0.9523
1.000 0.1159 0.03374 0.02282 -0.0284 0.8605 0.9622
1.250 0.1583 0.03392 0.02301 -0.0324 0.8535 0.9736
1.500 0.2094 0.03405 0.02316 -0.0379 0.8484 0.9838
1.750 0.2578 0.03416 0.02331 -0.0429 0.8425 0.9940
2.000 0.2921 0.03422 0.02340 -0.0453 0.8348 1.0000
2.250 0.3043 0.03423 0.02343 -0.0434 0.8251 1.0000
2.500 0.3308 0.03414 0.02336 -0.0437 0.8180 1.0000
2.750 0.3382 0.03421 0.02345 -0.0409 0.8066 1.0000
3.000 0.3513 0.03425 0.02353 -0.0389 0.7964 1.0000
3.250 0.3811 0.03409 0.02343 -0.0394 0.7892 1.0000
3.500 0.3891 0.03418 0.02355 -0.0364 0.7772 1.0000
3.750 0.4009 0.03423 0.02364 -0.0340 0.7657 1.0000
4.000 0.4193 0.03418 0.02365 -0.0325 0.7553 1.0000
4.250 0.4483 0.03391 0.02350 -0.0324 0.7467 1.0000
4.500 0.4605 0.03391 0.02357 -0.0299 0.7339 1.0000
4.750 0.4750 0.03388 0.02361 -0.0276 0.7213 1.0000
5.000 0.4921 0.03378 0.02359 -0.0256 0.7087 1.0000
5.250 0.5120 0.03358 0.02352 -0.0240 0.6962 1.0000
5.500 0.5352 0.03325 0.02330 -0.0226 0.6838 1.0000
5.750 0.5616 0.03276 0.02294 -0.0216 0.6715 1.0000
6.000 0.5853 0.03233 0.02265 -0.0202 0.6573 1.0000
6.250 0.6058 0.03203 0.02247 -0.0183 0.6412 1.0000
6.500 0.6284 0.03162 0.02224 -0.0167 0.6242 1.0000
6.750 0.6548 0.03103 0.02181 -0.0154 0.6064 1.0000
7.000 0.6833 0.03035 0.02127 -0.0142 0.5865 1.0000
7.250 0.7033 0.03008 0.02113 -0.0122 0.5620 1.0000
7.500 0.7252 0.02978 0.02092 -0.0104 0.5340 1.0000
7.750 0.7504 0.02938 0.02059 -0.0089 0.5014 1.0000
8.000 0.7691 0.02940 0.02059 -0.0068 0.4640 1.0000
8.250 0.7873 0.02957 0.02063 -0.0047 0.4233 1.0000
8.500 0.8007 0.03012 0.02099 -0.0023 0.3828 1.0000
8.750 0.8099 0.03100 0.02170 0.0002 0.3450 1.0000
9.000 0.8169 0.03209 0.02263 0.0028 0.3095 1.0000
9.250 0.8224 0.03334 0.02374 0.0052 0.2764 1.0000
9.500 0.8281 0.03470 0.02502 0.0075 0.2467 1.0000
9.750 0.8335 0.03617 0.02638 0.0096 0.2192 1.0000
10.000 0.8392 0.03772 0.02782 0.0115 0.1951 1.0000
10.250 0.8442 0.03938 0.02940 0.0132 0.1723 1.0000
10.500 0.8509 0.04108 0.03105 0.0148 0.1525 1.0000
10.750 0.8572 0.04288 0.03282 0.0162 0.1342 1.0000
11.000 0.8650 0.04470 0.03463 0.0175 0.1194 1.0000
11.250 0.8724 0.04660 0.03653 0.0187 0.1060 1.0000
11.500 0.8811 0.04853 0.03851 0.0198 0.0946 1.0000
11.750 0.8901 0.05052 0.04053 0.0208 0.0851 1.0000
12.000 0.8973 0.05258 0.04269 0.0217 0.0769 1.0000
12.250 0.9110 0.05470 0.04503 0.0226 0.0698 1.0000
12.500 0.9175 0.05692 0.04727 0.0234 0.0641 1.0000
12.750 0.9245 0.05954 0.05013 0.0241 0.0589 1.0000
13.000 0.9316 0.06228 0.05312 0.0248 0.0552 1.0000
13.250 0.9375 0.06492 0.05584 0.0253 0.0524 1.0000
13.500 0.9391 0.06815 0.05920 0.0257 0.0497 1.0000
13.750 0.9319 0.07219 0.06362 0.0258 0.0479 1.0000
14.000 0.9212 0.07662 0.06836 0.0255 0.0463 1.0000
14.250 0.9086 0.08144 0.07345 0.0246 0.0451 1.0000
14.500 0.8939 0.08680 0.07906 0.0230 0.0444 1.0000
14.750 0.8755 0.09304 0.08553 0.0205 0.0440 1.0000
15.000 0.8512 0.10082 0.09355 0.0167 0.0441 1.0000
15.250 0.8194 0.11116 0.10413 0.0109 0.0454 1.0000
15.500 0.7852 0.12361 0.11672 0.0035 0.0469 1.0000
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