NREL's S832 Airfoil (s832-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S832 Airfoil (s832-nr) Reynolds number: 1,000,000 Max Cl/Cd: 163.33 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s832-nr-1000000.txt Download as CSV file: xf-s832-nr-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.0373 0.08974 0.08706 -0.1105 0.7641 0.0065
-10.750 0.0422 0.08663 0.08393 -0.1117 0.7619 0.0065
-10.500 0.0030 0.09392 0.09107 -0.1227 0.7746 0.0062
-10.250 0.0088 0.09106 0.08822 -0.1240 0.7718 0.0062
-10.000 0.0140 0.08815 0.08531 -0.1252 0.7689 0.0062
-9.750 0.0188 0.08522 0.08238 -0.1264 0.7659 0.0064
-9.500 0.0229 0.08224 0.07937 -0.1276 0.7629 0.0066
-9.250 0.0271 0.07921 0.07636 -0.1290 0.7603 0.0067
-9.000 0.0290 0.07574 0.07291 -0.1308 0.7574 0.0069
-8.750 0.0313 0.07263 0.06980 -0.1324 0.7544 0.0069
-8.500 0.0327 0.06942 0.06660 -0.1341 0.7513 0.0070
-8.250 0.0315 0.06579 0.06296 -0.1365 0.7480 0.0070
-8.000 0.0275 0.06236 0.05955 -0.1392 0.7454 0.0070
-7.750 0.0195 0.05943 0.05663 -0.1399 0.7422 0.0070
-7.500 0.0155 0.05648 0.05363 -0.1400 0.7393 0.0070
-7.250 0.0171 0.05335 0.05043 -0.1404 0.7364 0.0071
-7.000 0.0213 0.05031 0.04730 -0.1405 0.7335 0.0071
-6.750 0.0281 0.04734 0.04426 -0.1404 0.7312 0.0071
-6.500 0.0361 0.04408 0.04091 -0.1399 0.7287 0.0071
-6.250 0.0369 0.03964 0.03632 -0.1388 0.7262 0.0073
-6.000 0.0475 0.03725 0.03381 -0.1382 0.7239 0.0074
-5.750 0.0619 0.03519 0.03163 -0.1376 0.7215 0.0076
-5.500 0.0777 0.03304 0.02934 -0.1370 0.7192 0.0078
-5.250 0.0949 0.03088 0.02706 -0.1362 0.7172 0.0081
-5.000 0.1130 0.02854 0.02457 -0.1353 0.7149 0.0085
-4.750 0.1325 0.02600 0.02182 -0.1340 0.7127 0.0092
-4.500 0.1571 0.02333 0.01885 -0.1321 0.7105 0.0100
-4.250 0.1662 0.01633 0.01119 -0.1283 0.7085 0.0067
-4.000 0.1888 0.01343 0.00780 -0.1269 0.7063 0.0067
-3.750 0.2153 0.01261 0.00678 -0.1266 0.7044 0.0072
-3.500 0.2399 0.01142 0.00544 -0.1262 0.7026 0.0074
-3.250 0.2652 0.01076 0.00471 -0.1259 0.7005 0.0077
-3.000 0.2908 0.01030 0.00421 -0.1257 0.6984 0.0079
-2.750 0.3170 0.01001 0.00389 -0.1256 0.6964 0.0085
-2.500 0.3436 0.00980 0.00364 -0.1257 0.6943 0.0093
-2.250 0.3695 0.00947 0.00322 -0.1255 0.6920 0.0096
-2.000 0.3957 0.00918 0.00290 -0.1254 0.6902 0.0099
-1.750 0.4219 0.00888 0.00256 -0.1253 0.6884 0.0108
-1.500 0.4483 0.00859 0.00233 -0.1252 0.6864 0.0286
-1.250 0.4756 0.00849 0.00227 -0.1254 0.6845 0.0416
-1.000 0.5031 0.00839 0.00220 -0.1257 0.6826 0.0574
-0.750 0.5289 0.00806 0.00214 -0.1258 0.6807 0.1611
-0.500 0.5434 0.00641 0.00216 -0.1244 0.6785 0.7666
-0.250 0.5703 0.00647 0.00226 -0.1243 0.6765 0.8033
0.000 0.5972 0.00652 0.00234 -0.1242 0.6748 0.8209
0.250 0.6247 0.00658 0.00239 -0.1243 0.6729 0.8319
0.500 0.6519 0.00666 0.00246 -0.1243 0.6710 0.8421
0.750 0.6790 0.00672 0.00252 -0.1243 0.6692 0.8497
1.000 0.7065 0.00678 0.00257 -0.1245 0.6674 0.8559
1.250 0.7342 0.00685 0.00261 -0.1247 0.6655 0.8615
1.500 0.7629 0.00694 0.00266 -0.1253 0.6633 0.8638
1.750 0.7905 0.00697 0.00269 -0.1256 0.6617 0.8658
2.000 0.8183 0.00700 0.00273 -0.1259 0.6600 0.8681
2.250 0.8462 0.00704 0.00278 -0.1263 0.6581 0.8705
2.500 0.8744 0.00708 0.00282 -0.1268 0.6563 0.8728
2.750 0.9024 0.00712 0.00286 -0.1272 0.6545 0.8750
3.000 0.9300 0.00716 0.00291 -0.1275 0.6526 0.8771
3.250 0.9582 0.00724 0.00297 -0.1280 0.6507 0.8793
3.500 0.9866 0.00733 0.00307 -0.1285 0.6487 0.8815
3.750 1.0133 0.00738 0.00316 -0.1287 0.6471 0.8842
4.000 1.0404 0.00743 0.00325 -0.1290 0.6451 0.8870
4.250 1.0675 0.00747 0.00332 -0.1292 0.6429 0.8895
4.500 1.0924 0.00746 0.00331 -0.1290 0.6382 0.8922
4.750 1.1144 0.00745 0.00333 -0.1281 0.6302 0.8953
5.000 1.1367 0.00747 0.00334 -0.1272 0.6222 0.8986
5.250 1.1610 0.00752 0.00343 -0.1269 0.6176 0.9019
5.500 1.1851 0.00756 0.00353 -0.1266 0.6135 0.9053
5.750 1.2085 0.00763 0.00362 -0.1260 0.6095 0.9088
6.000 1.2313 0.00770 0.00373 -0.1254 0.6047 0.9127
6.250 1.2536 0.00777 0.00385 -0.1247 0.5990 0.9168
6.500 1.2734 0.00787 0.00397 -0.1234 0.5934 0.9213
6.750 1.2919 0.00791 0.00409 -0.1219 0.5874 0.9269
7.000 1.3065 0.00803 0.00424 -0.1195 0.5801 0.9340
7.250 1.3207 0.00814 0.00442 -0.1171 0.5711 0.9428
7.500 1.3323 0.00831 0.00463 -0.1142 0.5612 0.9556
7.750 1.3498 0.00856 0.00491 -0.1127 0.5460 0.9783
8.000 1.3658 0.00898 0.00529 -0.1113 0.5254 1.0000
8.250 1.3667 0.00976 0.00593 -0.1071 0.4917 1.0000
8.500 1.3524 0.01119 0.00711 -0.1004 0.4419 1.0000
8.750 1.3398 0.01279 0.00850 -0.0945 0.3994 1.0000
9.000 1.3220 0.01484 0.01029 -0.0883 0.3515 1.0000
9.250 1.3064 0.01699 0.01220 -0.0828 0.3038 1.0000
9.500 1.3017 0.01873 0.01379 -0.0790 0.2712 1.0000
9.750 1.2918 0.02085 0.01570 -0.0749 0.2306 1.0000
10.000 1.2894 0.02265 0.01735 -0.0718 0.2007 1.0000
10.250 1.2783 0.02507 0.01950 -0.0680 0.1572 1.0000
10.500 1.2878 0.02624 0.02066 -0.0665 0.1461 1.0000
10.750 1.2856 0.02823 0.02247 -0.0639 0.1169 1.0000
11.000 1.2918 0.02971 0.02388 -0.0623 0.1012 1.0000
11.250 1.2990 0.03115 0.02527 -0.0608 0.0875 1.0000
11.500 1.3071 0.03256 0.02664 -0.0595 0.0759 1.0000
11.750 1.3146 0.03403 0.02808 -0.0581 0.0650 1.0000
12.000 1.3192 0.03575 0.02970 -0.0566 0.0498 1.0000
12.250 1.3278 0.03721 0.03115 -0.0555 0.0423 1.0000
12.500 1.3362 0.03871 0.03263 -0.0544 0.0357 1.0000
12.750 1.3431 0.04035 0.03423 -0.0533 0.0274 1.0000
13.000 1.3530 0.04178 0.03569 -0.0525 0.0237 1.0000
13.250 1.3607 0.04340 0.03729 -0.0515 0.0181 1.0000
13.500 1.3679 0.04511 0.03899 -0.0506 0.0139 1.0000
13.750 1.3749 0.04686 0.04074 -0.0497 0.0097 1.0000
14.000 1.3689 0.04985 0.04366 -0.0479 0.0013 1.0000
14.250 1.3768 0.05161 0.04548 -0.0471 0.0009 1.0000
14.500 1.3922 0.05267 0.04661 -0.0471 0.0019 1.0000
14.750 1.3918 0.05531 0.04932 -0.0459 0.0006 1.0000
15.000 1.4003 0.05709 0.05118 -0.0454 0.0006 1.0000
15.250 1.4020 0.05965 0.05386 -0.0445 0.0005 1.0000
15.500 1.4028 0.06233 0.05665 -0.0437 0.0004 1.0000
15.750 1.4110 0.06425 0.05863 -0.0435 0.0004 1.0000
16.000 1.4126 0.06695 0.06146 -0.0429 0.0004 1.0000
16.250 1.4155 0.06958 0.06419 -0.0426 0.0004 1.0000
16.500 1.4168 0.07243 0.06715 -0.0423 0.0004 1.0000
16.750 1.4191 0.07521 0.07002 -0.0422 0.0004 1.0000
17.000 1.4203 0.07818 0.07309 -0.0421 0.0004 1.0000
17.250 1.4186 0.08159 0.07662 -0.0421 0.0004 1.0000
17.500 1.4194 0.08474 0.07987 -0.0423 0.0004 1.0000
17.750 1.4169 0.08841 0.08365 -0.0425 0.0004 1.0000
18.000 1.4099 0.09279 0.08818 -0.0430 0.0003 1.0000
18.250 1.4071 0.09663 0.09213 -0.0436 0.0003 1.0000
18.500 1.3982 0.10149 0.09713 -0.0444 0.0003 1.0000
18.750 1.3951 0.10555 0.10131 -0.0454 0.0003 1.0000
19.000 1.3897 0.11003 0.10591 -0.0465 0.0003 1.0000
19.250 1.3817 0.11505 0.11106 -0.0480 0.0003 1.0000
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