S1091 (s1091-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 200,000 Max Cl/Cd: 90.71 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1091-il-200000-n5.txt Download as CSV file: xf-s1091-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1091
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2909 0.09835 0.09501 -0.0162 1.0000 0.0115
-6.750 -0.2943 0.09679 0.09349 -0.0145 1.0000 0.0115
-6.500 -0.2988 0.09520 0.09197 -0.0125 1.0000 0.0117
-6.250 -0.2751 0.09139 0.08816 -0.0180 0.9960 0.0120
-6.000 -0.2505 0.08750 0.08428 -0.0235 0.9913 0.0123
-5.750 -0.2246 0.08370 0.08047 -0.0294 0.9865 0.0128
-5.500 -0.1988 0.07992 0.07669 -0.0352 0.9813 0.0136
-5.250 -0.1697 0.07610 0.07286 -0.0418 0.9753 0.0144
-5.000 -0.1191 0.07243 0.06913 -0.0564 0.9674 0.0154
-4.750 -0.1085 0.06806 0.06481 -0.0554 0.9624 0.0164
-4.500 -0.0808 0.06465 0.06139 -0.0599 0.9568 0.0175
-4.250 -0.0505 0.06116 0.05786 -0.0652 0.9490 0.0187
-4.000 -0.0156 0.05755 0.05421 -0.0714 0.9416 0.0200
-3.750 0.0421 0.05362 0.05015 -0.0834 0.9350 0.0218
-3.500 0.0856 0.04995 0.04640 -0.0905 0.9274 0.0221
-3.250 0.1160 0.04516 0.04158 -0.0950 0.9213 0.0229
-3.000 0.1442 0.04238 0.03877 -0.0975 0.9131 0.0241
-2.750 0.1860 0.03914 0.03544 -0.1030 0.9075 0.0258
-2.500 0.2325 0.03559 0.03175 -0.1093 0.9002 0.0278
-2.250 0.2978 0.02873 0.02447 -0.1188 0.8950 0.0151
-2.000 0.3447 0.02486 0.02034 -0.1242 0.8877 0.0138
-1.750 0.3948 0.02019 0.01513 -0.1293 0.8799 0.0128
-1.500 0.4396 0.01666 0.01090 -0.1325 0.8698 0.0129
-1.250 0.4811 0.01505 0.00865 -0.1347 0.8570 0.0155
-1.000 0.5189 0.01342 0.00665 -0.1366 0.8417 0.0176
-0.750 0.5537 0.01244 0.00538 -0.1375 0.8252 0.0191
-0.500 0.5857 0.01193 0.00465 -0.1379 0.8085 0.0220
-0.250 0.6155 0.01134 0.00393 -0.1379 0.7925 0.0255
0.000 0.6440 0.01108 0.00351 -0.1377 0.7767 0.0288
0.250 0.6715 0.01088 0.00321 -0.1373 0.7614 0.0376
0.500 0.6986 0.01065 0.00304 -0.1368 0.7468 0.0843
0.750 0.7249 0.01051 0.00306 -0.1364 0.7325 0.1717
1.000 0.7509 0.01038 0.00313 -0.1359 0.7183 0.2756
1.250 0.7758 0.01027 0.00322 -0.1351 0.7041 0.3905
1.500 0.8011 0.01020 0.00325 -0.1344 0.6892 0.4958
2.000 0.8566 0.00971 0.00321 -0.1338 0.6562 1.0000
2.250 0.8816 0.00989 0.00325 -0.1329 0.6380 1.0000
2.500 0.9062 0.01010 0.00331 -0.1320 0.6181 1.0000
2.750 0.9305 0.01030 0.00340 -0.1311 0.5955 1.0000
3.000 0.9545 0.01053 0.00351 -0.1301 0.5704 1.0000
3.250 0.9779 0.01078 0.00362 -0.1290 0.5408 1.0000
3.500 1.0004 0.01110 0.00374 -0.1277 0.5038 1.0000
3.750 1.0221 0.01149 0.00391 -0.1264 0.4646 1.0000
4.000 1.0436 0.01193 0.00413 -0.1250 0.4270 1.0000
4.500 1.0865 0.01291 0.00474 -0.1225 0.3550 1.0000
4.750 1.1082 0.01340 0.00507 -0.1214 0.3234 1.0000
5.000 1.1299 0.01390 0.00542 -0.1203 0.2928 1.0000
5.250 1.1514 0.01443 0.00579 -0.1192 0.2627 1.0000
5.500 1.1728 0.01498 0.00624 -0.1180 0.2323 1.0000
5.750 1.1939 0.01555 0.00668 -0.1169 0.2037 1.0000
6.000 1.2151 0.01613 0.00715 -0.1158 0.1795 1.0000
6.250 1.2363 0.01670 0.00764 -0.1147 0.1591 1.0000
6.500 1.2572 0.01730 0.00820 -0.1135 0.1413 1.0000
6.750 1.2779 0.01790 0.00877 -0.1124 0.1266 1.0000
7.000 1.2986 0.01850 0.00935 -0.1112 0.1146 1.0000
7.250 1.3188 0.01913 0.00998 -0.1099 0.1045 1.0000
7.500 1.3383 0.01982 0.01064 -0.1086 0.0961 1.0000
7.750 1.3584 0.02041 0.01133 -0.1074 0.0893 1.0000
8.000 1.3767 0.02117 0.01210 -0.1059 0.0840 1.0000
8.250 1.3960 0.02181 0.01284 -0.1045 0.0803 1.0000
8.500 1.4145 0.02251 0.01363 -0.1030 0.0767 1.0000
8.750 1.4315 0.02331 0.01449 -0.1013 0.0737 1.0000
9.000 1.4464 0.02429 0.01553 -0.0994 0.0711 1.0000
9.250 1.4636 0.02506 0.01644 -0.0977 0.0693 1.0000
9.500 1.4798 0.02589 0.01742 -0.0959 0.0674 1.0000
9.750 1.4949 0.02674 0.01840 -0.0940 0.0654 1.0000
10.000 1.5087 0.02760 0.01937 -0.0919 0.0633 1.0000
10.250 1.5208 0.02859 0.02047 -0.0897 0.0615 1.0000
10.500 1.5311 0.02983 0.02178 -0.0872 0.0599 1.0000
10.750 1.5430 0.03096 0.02306 -0.0851 0.0585 1.0000
11.000 1.5560 0.03176 0.02407 -0.0831 0.0562 1.0000
11.250 1.5680 0.03245 0.02492 -0.0811 0.0526 1.0000
11.500 1.5770 0.03339 0.02593 -0.0790 0.0495 1.0000
11.750 1.5864 0.03446 0.02715 -0.0770 0.0465 1.0000
12.000 1.5988 0.03528 0.02818 -0.0754 0.0430 1.0000
12.500 1.6240 0.03692 0.02994 -0.0729 0.0249 1.0000
12.750 1.6206 0.03945 0.03230 -0.0706 0.0109 1.0000
13.000 1.6119 0.04270 0.03562 -0.0682 0.0057 1.0000
13.250 1.6048 0.04593 0.03901 -0.0664 0.0038 1.0000
13.500 1.5989 0.04919 0.04248 -0.0650 0.0030 1.0000
13.750 1.5901 0.05303 0.04652 -0.0642 0.0025 1.0000
14.000 1.5830 0.05680 0.05051 -0.0638 0.0024 1.0000
14.250 1.5739 0.06107 0.05502 -0.0639 0.0022 1.0000
14.500 1.5637 0.06572 0.05991 -0.0645 0.0021 1.0000
14.750 1.5516 0.07090 0.06532 -0.0657 0.0020 1.0000
15.000 1.5371 0.07682 0.07147 -0.0676 0.0019 1.0000
15.250 1.5218 0.08323 0.07810 -0.0701 0.0019 1.0000
15.500 1.5034 0.09067 0.08577 -0.0735 0.0019 1.0000
15.750 1.4844 0.09874 0.09406 -0.0776 0.0019 1.0000
16.000 1.4627 0.10792 0.10346 -0.0826 0.0019 1.0000
16.250 1.4401 0.11778 0.11353 -0.0882 0.0021 1.0000
16.500 1.4145 0.12887 0.12482 -0.0947 0.0022 1.0000
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Polar data table (+)
Polar graphs
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