NREL's S833 Airfoil (s833-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S833 Airfoil (s833-nr) Reynolds number: 50,000 Max Cl/Cd: 23.64 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s833-nr-50000-n5.txt Download as CSV file: xf-s833-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S833 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6227 0.11163 0.10291 -0.0532 1.0000 0.1687
-13.000 -0.6035 0.11263 0.10387 -0.0510 1.0000 0.1715
-12.500 -0.6633 0.09686 0.08814 -0.0551 1.0000 0.1847
-12.250 -0.6449 0.09789 0.08912 -0.0528 1.0000 0.1878
-12.000 -0.8024 0.07230 0.06359 -0.0614 1.0000 0.1994
-11.750 -0.7321 0.07976 0.07104 -0.0569 1.0000 0.2028
-11.500 -0.7954 0.06987 0.06112 -0.0582 1.0000 0.2092
-11.250 -0.8909 0.05908 0.05016 -0.0573 1.0000 0.2130
-11.000 -0.8810 0.05860 0.04972 -0.0553 1.0000 0.2180
-10.750 -0.8910 0.05671 0.04779 -0.0528 1.0000 0.2230
-10.500 -0.9317 0.05300 0.04398 -0.0489 1.0000 0.2267
-10.250 -0.9753 0.04980 0.04062 -0.0437 1.0000 0.2297
-10.000 -0.9591 0.04976 0.04066 -0.0417 1.0000 0.2357
-9.750 -0.9698 0.04797 0.03878 -0.0387 1.0000 0.2411
-9.500 -0.9835 0.04577 0.03639 -0.0357 1.0000 0.2470
-9.250 -0.9708 0.04543 0.03611 -0.0337 1.0000 0.2535
-9.000 -0.9762 0.04358 0.03405 -0.0313 1.0000 0.2609
-8.750 -0.9643 0.04304 0.03355 -0.0294 1.0000 0.2677
-8.500 -0.9597 0.04177 0.03214 -0.0276 1.0000 0.2757
-8.250 -0.9487 0.04104 0.03137 -0.0259 1.0000 0.2834
-8.000 -0.9400 0.04000 0.03020 -0.0244 1.0000 0.2923
-7.750 -0.9265 0.03938 0.02956 -0.0229 1.0000 0.3002
-7.500 -0.9155 0.03836 0.02840 -0.0217 1.0000 0.3099
-7.250 -0.8998 0.03799 0.02804 -0.0203 1.0000 0.3183
-7.000 -0.8868 0.03698 0.02686 -0.0195 1.0000 0.3289
-6.750 -0.8651 0.03685 0.02675 -0.0189 0.9985 0.3378
-6.500 -0.8379 0.03652 0.02633 -0.0200 0.9945 0.3495
-6.250 -0.8115 0.03598 0.02562 -0.0213 0.9905 0.3621
-6.000 -0.7845 0.03606 0.02572 -0.0216 0.9865 0.3724
-5.750 -0.7562 0.03595 0.02555 -0.0226 0.9827 0.3842
-5.500 -0.7306 0.03555 0.02502 -0.0235 0.9784 0.3967
-5.250 -0.7041 0.03558 0.02504 -0.0237 0.9741 0.4079
-5.000 -0.6751 0.03567 0.02510 -0.0246 0.9703 0.4195
-4.750 -0.6505 0.03541 0.02476 -0.0249 0.9657 0.4319
-4.500 -0.6242 0.03533 0.02463 -0.0254 0.9611 0.4444
-4.250 -0.5952 0.03564 0.02495 -0.0258 0.9572 0.4552
-4.000 -0.5713 0.03554 0.02481 -0.0258 0.9524 0.4672
-3.750 -0.5450 0.03541 0.02460 -0.0264 0.9476 0.4805
-3.500 -0.5162 0.03588 0.02510 -0.0265 0.9436 0.4907
-3.250 -0.4934 0.03591 0.02511 -0.0261 0.9384 0.5020
-3.000 -0.4671 0.03588 0.02503 -0.0266 0.9334 0.5150
-2.750 -0.4379 0.03636 0.02552 -0.0268 0.9293 0.5254
-2.500 -0.4169 0.03644 0.02559 -0.0260 0.9236 0.5360
-2.250 -0.3899 0.03650 0.02560 -0.0265 0.9185 0.5489
-2.000 -0.3599 0.03704 0.02615 -0.0268 0.9145 0.5587
-1.750 -0.3413 0.03708 0.02619 -0.0256 0.9080 0.5691
-1.500 -0.3126 0.03722 0.02627 -0.0264 0.9031 0.5821
-1.250 -0.2880 0.03770 0.02679 -0.0256 0.8981 0.5904
-1.000 -0.2659 0.03780 0.02687 -0.0251 0.8916 0.6016
-0.750 -0.2355 0.03803 0.02707 -0.0261 0.8869 0.6137
-0.500 -0.2159 0.03836 0.02743 -0.0246 0.8804 0.6220
-0.250 -0.1893 0.03849 0.02754 -0.0250 0.8744 0.6339
0.000 -0.1579 0.03885 0.02791 -0.0257 0.8701 0.6440
0.250 -0.1418 0.03898 0.02805 -0.0241 0.8619 0.6537
0.500 -0.1103 0.03909 0.02814 -0.0255 0.8565 0.6662
0.750 -0.0909 0.03940 0.02850 -0.0239 0.8495 0.6738
1.000 -0.0645 0.03950 0.02860 -0.0243 0.8426 0.6852
1.250 -0.0325 0.03974 0.02887 -0.0248 0.8380 0.6944
1.500 -0.0175 0.03985 0.02902 -0.0233 0.8283 0.7042
1.750 0.0143 0.03997 0.02917 -0.0241 0.8229 0.7145
2.000 0.0301 0.04014 0.02939 -0.0225 0.8136 0.7232
2.250 0.0628 0.04018 0.02944 -0.0238 0.8074 0.7345
2.500 0.0786 0.04036 0.02970 -0.0218 0.7981 0.7422
2.750 0.1108 0.04036 0.02974 -0.0229 0.7914 0.7530
3.000 0.1275 0.04050 0.02996 -0.0211 0.7816 0.7609
3.250 0.1598 0.04045 0.02996 -0.0221 0.7746 0.7710
3.500 0.1767 0.04057 0.03016 -0.0205 0.7641 0.7794
3.750 0.2105 0.04040 0.03007 -0.0214 0.7572 0.7888
4.000 0.2266 0.04054 0.03028 -0.0198 0.7455 0.7976
4.250 0.2632 0.04019 0.03003 -0.0208 0.7394 0.8065
4.500 0.2789 0.04032 0.03025 -0.0193 0.7265 0.8154
4.750 0.3005 0.04028 0.03030 -0.0184 0.7154 0.8239
5.000 0.3345 0.03984 0.02998 -0.0190 0.7072 0.8330
5.250 0.3516 0.03985 0.03010 -0.0174 0.6939 0.8413
5.500 0.3767 0.03969 0.03004 -0.0170 0.6820 0.8505
5.750 0.4096 0.03891 0.02941 -0.0167 0.6735 0.8587
6.000 0.4304 0.03883 0.02944 -0.0158 0.6592 0.8677
6.250 0.4513 0.03852 0.02927 -0.0144 0.6455 0.8764
6.500 0.4787 0.03794 0.02884 -0.0137 0.6331 0.8853
6.750 0.5144 0.03681 0.02786 -0.0135 0.6230 0.8944
7.000 0.5374 0.03635 0.02755 -0.0123 0.6073 0.9035
7.250 0.5637 0.03577 0.02713 -0.0115 0.5911 0.9131
7.500 0.5918 0.03506 0.02657 -0.0107 0.5740 0.9229
7.750 0.6240 0.03423 0.02590 -0.0104 0.5555 0.9330
8.000 0.6497 0.03395 0.02575 -0.0099 0.5319 0.9439
8.250 0.6853 0.03323 0.02513 -0.0104 0.5064 0.9556
8.500 0.7185 0.03284 0.02482 -0.0110 0.4757 0.9704
8.750 0.7462 0.03253 0.02447 -0.0109 0.4435 1.0000
9.000 0.7707 0.03282 0.02466 -0.0107 0.4104 1.0000
9.250 0.7911 0.03346 0.02518 -0.0104 0.3773 1.0000
9.500 0.8084 0.03438 0.02598 -0.0098 0.3454 1.0000
9.750 0.8236 0.03549 0.02695 -0.0092 0.3153 1.0000
10.000 0.8367 0.03681 0.02817 -0.0086 0.2869 1.0000
10.250 0.8492 0.03826 0.02954 -0.0081 0.2604 1.0000
10.500 0.8608 0.03982 0.03099 -0.0076 0.2364 1.0000
10.750 0.8722 0.04148 0.03260 -0.0072 0.2140 1.0000
11.000 0.8833 0.04324 0.03432 -0.0068 0.1933 1.0000
11.250 0.8938 0.04509 0.03612 -0.0065 0.1750 1.0000
11.500 0.9042 0.04701 0.03800 -0.0062 0.1586 1.0000
11.750 0.9146 0.04901 0.03998 -0.0060 0.1438 1.0000
12.000 0.9251 0.05107 0.04205 -0.0058 0.1307 1.0000
12.250 0.9356 0.05318 0.04418 -0.0057 0.1195 1.0000
12.500 0.9455 0.05533 0.04626 -0.0056 0.1100 1.0000
12.750 0.9557 0.05760 0.04867 -0.0055 0.1007 1.0000
13.000 0.9660 0.05994 0.05109 -0.0054 0.0930 1.0000
13.250 0.9747 0.06230 0.05345 -0.0055 0.0865 1.0000
13.500 0.9837 0.06495 0.05628 -0.0055 0.0805 1.0000
13.750 0.9904 0.06757 0.05898 -0.0056 0.0756 1.0000
14.000 0.9971 0.07047 0.06201 -0.0058 0.0714 1.0000
14.250 0.9998 0.07380 0.06558 -0.0061 0.0676 1.0000
14.500 1.0051 0.07663 0.06842 -0.0065 0.0645 1.0000
14.750 1.0053 0.08046 0.07245 -0.0072 0.0619 1.0000
15.000 0.9981 0.08523 0.07754 -0.0083 0.0599 1.0000
15.250 0.9907 0.09005 0.08259 -0.0099 0.0580 1.0000
15.500 0.9858 0.09456 0.08725 -0.0116 0.0564 1.0000
15.750 0.9911 0.09759 0.09020 -0.0126 0.0545 1.0000
16.000 0.9693 0.10513 0.09809 -0.0163 0.0539 1.0000
16.250 0.9446 0.11375 0.10701 -0.0211 0.0537 1.0000
16.500 0.9150 0.12414 0.11768 -0.0275 0.0538 1.0000
16.750 0.8770 0.13774 0.13151 -0.0363 0.0540 1.0000
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