NREL's S832 Airfoil (s832-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S832 Airfoil (s832-nr) Reynolds number: 1,000,000 Max Cl/Cd: 151.19 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s832-nr-1000000-n5.txt Download as CSV file: xf-s832-nr-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S832 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0109 0.08414 0.08110 -0.1258 0.7313 0.0047
-9.500 0.0151 0.08106 0.07804 -0.1271 0.7290 0.0047
-9.250 0.0190 0.07806 0.07504 -0.1284 0.7264 0.0047
-9.000 0.0214 0.07482 0.07181 -0.1298 0.7237 0.0047
-8.750 0.0240 0.07182 0.06880 -0.1312 0.7211 0.0047
-8.500 0.0256 0.06867 0.06566 -0.1327 0.7185 0.0047
-8.250 0.0236 0.06499 0.06202 -0.1349 0.7160 0.0047
-6.250 0.0176 0.03714 0.03359 -0.1361 0.6957 0.0027
-6.000 0.0275 0.03347 0.02971 -0.1347 0.6935 0.0027
-5.500 0.0226 0.01400 0.00845 -0.1241 0.6898 0.0031
-5.250 0.0481 0.01334 0.00768 -0.1241 0.6879 0.0033
-5.000 0.0737 0.01265 0.00686 -0.1239 0.6858 0.0034
-4.750 0.0996 0.01213 0.00625 -0.1238 0.6836 0.0035
-4.500 0.1255 0.01167 0.00569 -0.1238 0.6813 0.0037
-4.250 0.1511 0.01120 0.00512 -0.1236 0.6792 0.0039
-4.000 0.1766 0.01079 0.00461 -0.1234 0.6772 0.0040
-3.750 0.2028 0.01042 0.00419 -0.1233 0.6755 0.0042
-3.500 0.2289 0.01009 0.00381 -0.1233 0.6736 0.0043
-3.250 0.2554 0.00987 0.00355 -0.1233 0.6717 0.0046
-3.000 0.2817 0.00962 0.00326 -0.1232 0.6696 0.0048
-2.750 0.3073 0.00930 0.00289 -0.1231 0.6676 0.0052
-2.500 0.3337 0.00911 0.00267 -0.1231 0.6655 0.0055
-2.250 0.3601 0.00895 0.00246 -0.1230 0.6635 0.0058
-2.000 0.3872 0.00880 0.00229 -0.1232 0.6617 0.0063
-1.750 0.4145 0.00867 0.00214 -0.1233 0.6599 0.0070
-1.500 0.4415 0.00852 0.00201 -0.1234 0.6580 0.0147
-1.250 0.4687 0.00841 0.00195 -0.1236 0.6560 0.0242
-1.000 0.4959 0.00834 0.00190 -0.1238 0.6541 0.0345
-0.750 0.5229 0.00825 0.00186 -0.1240 0.6523 0.0515
-0.500 0.5498 0.00817 0.00181 -0.1241 0.6504 0.0758
-0.250 0.5724 0.00740 0.00178 -0.1240 0.6486 0.3649
0.000 0.5920 0.00632 0.00182 -0.1232 0.6467 0.7574
0.250 0.6196 0.00633 0.00186 -0.1234 0.6448 0.7826
0.500 0.6472 0.00637 0.00190 -0.1235 0.6429 0.7994
0.750 0.6745 0.00641 0.00195 -0.1237 0.6410 0.8113
1.000 0.7019 0.00646 0.00199 -0.1239 0.6392 0.8188
1.250 0.7294 0.00652 0.00203 -0.1241 0.6374 0.8260
1.500 0.7571 0.00659 0.00206 -0.1244 0.6356 0.8289
1.750 0.7849 0.00662 0.00210 -0.1247 0.6339 0.8309
2.000 0.8127 0.00665 0.00214 -0.1251 0.6320 0.8330
2.250 0.8404 0.00670 0.00219 -0.1254 0.6301 0.8350
2.500 0.8680 0.00675 0.00224 -0.1257 0.6283 0.8372
2.750 0.8955 0.00680 0.00231 -0.1260 0.6264 0.8393
3.000 0.9228 0.00686 0.00237 -0.1263 0.6246 0.8416
3.250 0.9499 0.00694 0.00243 -0.1265 0.6227 0.8438
3.500 0.9767 0.00701 0.00250 -0.1267 0.6208 0.8461
3.750 1.0038 0.00706 0.00260 -0.1269 0.6191 0.8483
4.000 1.0308 0.00711 0.00269 -0.1271 0.6172 0.8505
4.250 1.0574 0.00717 0.00278 -0.1273 0.6149 0.8529
4.500 1.0819 0.00725 0.00285 -0.1270 0.6096 0.8555
4.750 1.1038 0.00734 0.00294 -0.1261 0.5982 0.8584
5.000 1.1232 0.00747 0.00305 -0.1248 0.5843 0.8614
5.250 1.1437 0.00760 0.00318 -0.1236 0.5748 0.8644
5.500 1.1638 0.00771 0.00331 -0.1224 0.5675 0.8677
5.750 1.1838 0.00783 0.00345 -0.1212 0.5613 0.8711
6.000 1.2007 0.00802 0.00363 -0.1194 0.5518 0.8746
6.250 1.2161 0.00824 0.00386 -0.1173 0.5391 0.8786
6.500 1.2284 0.00855 0.00415 -0.1147 0.5234 0.8836
7.000 1.2379 0.00966 0.00511 -0.1068 0.4697 0.8962
7.250 1.2271 0.01079 0.00606 -0.1003 0.4259 0.9060
7.750 1.2094 0.01325 0.00828 -0.0889 0.3506 0.9408
8.250 1.2129 0.01607 0.01083 -0.0831 0.2803 1.0000
8.500 1.2155 0.01737 0.01203 -0.0802 0.2540 1.0000
8.750 1.2144 0.01893 0.01344 -0.0770 0.2230 1.0000
9.000 1.2155 0.02044 0.01482 -0.0742 0.1954 1.0000
9.250 1.2211 0.02174 0.01603 -0.0720 0.1747 1.0000
9.500 1.2264 0.02310 0.01731 -0.0699 0.1556 1.0000
9.750 1.2334 0.02439 0.01854 -0.0681 0.1385 1.0000
10.000 1.2384 0.02585 0.01990 -0.0661 0.1187 1.0000
10.250 1.2377 0.02773 0.02161 -0.0636 0.0905 1.0000
10.500 1.2514 0.02867 0.02259 -0.0627 0.0864 1.0000
10.750 1.2518 0.03057 0.02432 -0.0605 0.0606 1.0000
11.000 1.2559 0.03226 0.02592 -0.0588 0.0442 1.0000
11.250 1.2659 0.03356 0.02718 -0.0577 0.0366 1.0000
11.500 1.2773 0.03477 0.02841 -0.0567 0.0321 1.0000
11.750 1.2873 0.03609 0.02971 -0.0557 0.0264 1.0000
12.000 1.2937 0.03773 0.03132 -0.0544 0.0174 1.0000
12.250 1.3041 0.03908 0.03268 -0.0535 0.0145 1.0000
12.500 1.3163 0.04031 0.03394 -0.0528 0.0128 1.0000
12.750 1.3233 0.04197 0.03559 -0.0517 0.0081 1.0000
13.000 1.3347 0.04330 0.03695 -0.0511 0.0072 1.0000
13.250 1.3429 0.04493 0.03858 -0.0502 0.0045 1.0000
13.500 1.3517 0.04653 0.04022 -0.0494 0.0030 1.0000
13.750 1.3597 0.04823 0.04195 -0.0486 0.0012 1.0000
14.000 1.3650 0.05020 0.04397 -0.0477 0.0003 1.0000
14.250 1.3752 0.05174 0.04557 -0.0471 0.0002 1.0000
14.750 1.3919 0.05526 0.04921 -0.0460 0.0001 1.0000
15.000 1.4017 0.05692 0.05093 -0.0456 0.0001 1.0000
15.250 1.4066 0.05911 0.05321 -0.0450 0.0001 1.0000
15.500 1.4138 0.06107 0.05525 -0.0445 0.0001 1.0000
15.750 1.4216 0.06300 0.05724 -0.0442 0.0001 1.0000
16.000 1.4274 0.06518 0.05952 -0.0438 0.0001 1.0000
16.250 1.4336 0.06735 0.06178 -0.0435 0.0001 1.0000
16.500 1.4374 0.06983 0.06436 -0.0433 0.0000 1.0000
16.750 1.4434 0.07210 0.06669 -0.0431 0.0000 1.0000
17.000 1.4479 0.07458 0.06926 -0.0430 0.0000 1.0000
17.250 1.4493 0.07744 0.07223 -0.0429 0.0000 1.0000
17.500 1.4542 0.07994 0.07481 -0.0430 0.0000 1.0000
17.750 1.4564 0.08283 0.07779 -0.0431 0.0000 1.0000
18.000 1.4550 0.08625 0.08134 -0.0433 0.0000 1.0000
18.250 1.4557 0.08944 0.08462 -0.0436 0.0000 1.0000
18.500 1.4526 0.09319 0.08850 -0.0440 0.0000 1.0000
18.750 1.4538 0.09639 0.09180 -0.0446 0.0000 1.0000
19.000 1.4514 0.10017 0.09570 -0.0453 0.0000 1.0000
19.250 1.4482 0.10414 0.09979 -0.0462 0.0000 1.0000
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