NREL's S832 Airfoil (s832-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S832 Airfoil (s832-nr) Reynolds number: 500,000 Max Cl/Cd: 118.92 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s832-nr-500000-n5.txt Download as CSV file: xf-s832-nr-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.0376 0.08761 0.08420 -0.1110 0.7553 0.0076
-10.500 0.0422 0.08451 0.08110 -0.1121 0.7531 0.0078
-10.250 0.0462 0.08123 0.07781 -0.1132 0.7509 0.0078
-10.000 0.0501 0.07807 0.07463 -0.1143 0.7489 0.0078
-9.750 0.0537 0.07479 0.07135 -0.1155 0.7469 0.0079
-9.500 0.0568 0.07139 0.06796 -0.1167 0.7448 0.0080
-9.250 0.0596 0.06806 0.06464 -0.1178 0.7426 0.0080
-9.000 0.0615 0.06460 0.06119 -0.1190 0.7403 0.0082
-8.750 0.0634 0.06126 0.05785 -0.1202 0.7381 0.0082
-8.500 0.0643 0.05786 0.05444 -0.1215 0.7359 0.0082
-8.250 0.0637 0.05435 0.05093 -0.1228 0.7337 0.0084
-8.000 0.0627 0.05082 0.04742 -0.1245 0.7314 0.0082
-7.750 0.0593 0.04716 0.04379 -0.1266 0.7289 0.0081
-7.500 0.0501 0.04337 0.04000 -0.1296 0.7263 0.0081
-7.000 0.0112 0.05079 0.04702 -0.1385 0.7275 0.0071
-6.750 0.0288 0.03293 0.02936 -0.1305 0.7194 0.0066
-6.500 0.0314 0.02966 0.02602 -0.1303 0.7169 0.0062
-6.250 0.0236 0.04019 0.03601 -0.1363 0.7204 0.0047
-6.000 0.0341 0.03709 0.03274 -0.1353 0.7182 0.0046
-5.750 0.0467 0.03411 0.02958 -0.1342 0.7156 0.0045
-5.500 0.0605 0.03087 0.02611 -0.1328 0.7131 0.0045
-5.250 0.0750 0.02727 0.02221 -0.1309 0.7108 0.0045
-5.000 0.0864 0.02090 0.01520 -0.1274 0.7087 0.0047
-4.750 0.1052 0.01719 0.01091 -0.1256 0.7068 0.0050
-4.500 0.1299 0.01627 0.00979 -0.1253 0.7050 0.0053
-4.250 0.1550 0.01520 0.00853 -0.1250 0.7030 0.0055
-4.000 0.1806 0.01450 0.00769 -0.1248 0.7008 0.0060
-3.750 0.2065 0.01394 0.00699 -0.1246 0.6985 0.0068
-3.500 0.2322 0.01337 0.00628 -0.1243 0.6963 0.0071
-3.250 0.2570 0.01270 0.00550 -0.1239 0.6943 0.0071
-3.000 0.2812 0.01208 0.00479 -0.1234 0.6924 0.0074
-2.750 0.3061 0.01166 0.00432 -0.1231 0.6905 0.0077
-2.500 0.3314 0.01136 0.00399 -0.1229 0.6885 0.0081
-2.250 0.3571 0.01109 0.00368 -0.1227 0.6865 0.0089
-2.000 0.3829 0.01085 0.00340 -0.1226 0.6844 0.0104
-1.750 0.4089 0.01064 0.00318 -0.1225 0.6824 0.0150
-1.500 0.4353 0.01050 0.00306 -0.1225 0.6804 0.0264
-1.250 0.4620 0.01038 0.00299 -0.1226 0.6785 0.0428
-1.000 0.4888 0.01027 0.00288 -0.1227 0.6767 0.0567
-0.750 0.5149 0.01012 0.00282 -0.1228 0.6747 0.0883
-0.500 0.5261 0.00823 0.00280 -0.1209 0.6726 0.7135
-0.250 0.5505 0.00823 0.00294 -0.1202 0.6706 0.7846
0.000 0.5764 0.00830 0.00302 -0.1199 0.6687 0.8080
0.250 0.6026 0.00839 0.00308 -0.1196 0.6669 0.8260
0.500 0.6288 0.00847 0.00313 -0.1194 0.6651 0.8383
0.750 0.6559 0.00856 0.00317 -0.1195 0.6634 0.8472
1.000 0.6818 0.00863 0.00324 -0.1193 0.6614 0.8539
1.250 0.7091 0.00868 0.00328 -0.1195 0.6594 0.8571
1.500 0.7367 0.00873 0.00331 -0.1199 0.6575 0.8596
1.750 0.7637 0.00878 0.00335 -0.1200 0.6556 0.8615
2.000 0.7908 0.00883 0.00340 -0.1202 0.6538 0.8635
2.250 0.8182 0.00889 0.00344 -0.1205 0.6520 0.8656
2.500 0.8459 0.00896 0.00348 -0.1208 0.6502 0.8681
2.750 0.8734 0.00904 0.00355 -0.1212 0.6485 0.8709
3.000 0.9000 0.00911 0.00366 -0.1213 0.6465 0.8737
3.250 0.9261 0.00918 0.00376 -0.1214 0.6446 0.8759
3.500 0.9521 0.00925 0.00386 -0.1214 0.6426 0.8782
3.750 0.9783 0.00932 0.00396 -0.1214 0.6405 0.8808
4.000 1.0048 0.00940 0.00407 -0.1216 0.6385 0.8837
4.250 1.0320 0.00949 0.00417 -0.1219 0.6369 0.8867
4.750 1.0837 0.00967 0.00445 -0.1219 0.6330 0.8923
5.000 1.1079 0.00976 0.00461 -0.1216 0.6306 0.8955
5.250 1.1306 0.00982 0.00472 -0.1210 0.6260 0.8991
5.750 1.1631 0.00987 0.00480 -0.1168 0.6040 0.9085
6.000 1.1778 0.00995 0.00490 -0.1144 0.5949 0.9145
6.250 1.1951 0.01005 0.00507 -0.1127 0.5894 0.9200
6.500 1.2102 0.01019 0.00527 -0.1105 0.5826 0.9270
6.750 1.2256 0.01035 0.00549 -0.1084 0.5756 0.9353
7.000 1.2399 0.01053 0.00573 -0.1061 0.5672 0.9475
7.250 1.2584 0.01077 0.00603 -0.1049 0.5556 0.9651
7.500 1.2786 0.01109 0.00637 -0.1044 0.5412 1.0000
7.750 1.2879 0.01160 0.00683 -0.1016 0.5227 1.0000
8.000 1.2908 0.01236 0.00752 -0.0979 0.4952 1.0000
8.250 1.2808 0.01372 0.00868 -0.0924 0.4541 1.0000
8.500 1.2655 0.01556 0.01030 -0.0864 0.4114 1.0000
8.750 1.2530 0.01752 0.01207 -0.0814 0.3726 1.0000
9.000 1.2424 0.01957 0.01394 -0.0769 0.3355 1.0000
9.250 1.2373 0.02144 0.01566 -0.0734 0.3042 1.0000
9.500 1.2314 0.02346 0.01753 -0.0700 0.2706 1.0000
9.750 1.2279 0.02544 0.01936 -0.0670 0.2396 1.0000
10.000 1.2278 0.02726 0.02106 -0.0646 0.2124 1.0000
10.250 1.2309 0.02893 0.02264 -0.0626 0.1895 1.0000
10.500 1.2336 0.03066 0.02428 -0.0606 0.1673 1.0000
10.750 1.2384 0.03230 0.02584 -0.0589 0.1473 1.0000
11.000 1.2444 0.03389 0.02736 -0.0574 0.1304 1.0000
11.500 1.2585 0.03700 0.03039 -0.0548 0.1023 1.0000
11.750 1.2654 0.03861 0.03196 -0.0536 0.0883 1.0000
12.000 1.2700 0.04044 0.03369 -0.0523 0.0700 1.0000
12.250 1.2787 0.04197 0.03523 -0.0513 0.0616 1.0000
12.500 1.2870 0.04355 0.03680 -0.0504 0.0532 1.0000
12.750 1.2923 0.04542 0.03861 -0.0493 0.0409 1.0000
13.000 1.3026 0.04691 0.04014 -0.0486 0.0374 1.0000
13.250 1.3070 0.04892 0.04208 -0.0476 0.0270 1.0000
13.500 1.3125 0.05087 0.04400 -0.0467 0.0196 1.0000
13.750 1.3191 0.05275 0.04588 -0.0460 0.0143 1.0000
14.000 1.3246 0.05478 0.04792 -0.0452 0.0098 1.0000
14.250 1.3323 0.05664 0.04982 -0.0446 0.0076 1.0000
14.500 1.3411 0.05841 0.05167 -0.0442 0.0070 1.0000
14.750 1.3470 0.06049 0.05378 -0.0436 0.0048 1.0000
15.000 1.3543 0.06247 0.05584 -0.0432 0.0039 1.0000
15.250 1.3590 0.06477 0.05819 -0.0428 0.0023 1.0000
15.500 1.3631 0.06716 0.06065 -0.0423 0.0013 1.0000
15.750 1.3701 0.06927 0.06286 -0.0421 0.0013 1.0000
16.000 1.3726 0.07194 0.06560 -0.0417 0.0008 1.0000
16.250 1.3768 0.07446 0.06823 -0.0416 0.0007 1.0000
16.500 1.3777 0.07740 0.07130 -0.0414 0.0005 1.0000
16.750 1.3819 0.08000 0.07400 -0.0414 0.0005 1.0000
17.000 1.3838 0.08294 0.07707 -0.0414 0.0004 1.0000
17.250 1.3845 0.08608 0.08033 -0.0415 0.0003 1.0000
17.500 1.3872 0.08901 0.08337 -0.0418 0.0004 1.0000
17.750 1.3875 0.09227 0.08676 -0.0422 0.0003 1.0000
18.000 1.3848 0.09604 0.09068 -0.0427 0.0003 1.0000
18.250 1.3843 0.09955 0.09433 -0.0433 0.0003 1.0000
18.500 1.3803 0.10368 0.09860 -0.0441 0.0002 1.0000
18.750 1.3788 0.10744 0.10249 -0.0450 0.0003 1.0000
19.000 1.3759 0.11150 0.10668 -0.0461 0.0002 1.0000
19.250 1.3710 0.11594 0.11126 -0.0475 0.0002 1.0000
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