S1091 (s1091-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 500,000 Max Cl/Cd: 111.04 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1091-il-500000-n5.txt Download as CSV file: xf-s1091-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3146 0.11242 0.11010 -0.0178 1.0000 0.0063
-8.500 -0.3127 0.11032 0.10804 -0.0180 1.0000 0.0063
-8.250 -0.3100 0.10809 0.10583 -0.0178 1.0000 0.0063
-8.000 -0.3005 0.10528 0.10303 -0.0198 0.9992 0.0063
-7.750 -0.2851 0.10193 0.09968 -0.0232 0.9973 0.0063
-7.500 -0.2710 0.09758 0.09535 -0.0247 0.9960 0.0064
-7.250 -0.2557 0.09429 0.09206 -0.0276 0.9940 0.0065
-7.000 -0.2417 0.09122 0.08901 -0.0302 0.9911 0.0066
-6.750 -0.2257 0.08810 0.08589 -0.0335 0.9878 0.0067
-6.500 -0.2037 0.08451 0.08230 -0.0384 0.9853 0.0068
-6.250 -0.1862 0.08129 0.07910 -0.0419 0.9805 0.0068
-6.000 -0.1641 0.07787 0.07567 -0.0466 0.9763 0.0069
-5.750 -0.1377 0.07424 0.07204 -0.0523 0.9735 0.0072
-5.500 -0.1188 0.07120 0.06901 -0.0558 0.9667 0.0072
-5.250 -0.0920 0.06770 0.06549 -0.0612 0.9620 0.0073
-5.000 -0.0686 0.06449 0.06228 -0.0654 0.9546 0.0075
-4.750 -0.0401 0.06101 0.05878 -0.0707 0.9477 0.0078
-4.500 -0.0156 0.05786 0.05562 -0.0746 0.9370 0.0080
-4.250 0.0171 0.05434 0.05206 -0.0803 0.9289 0.0083
-4.000 0.0604 0.05027 0.04793 -0.0884 0.9216 0.0089
-3.750 0.1135 0.04574 0.04331 -0.0986 0.9141 0.0092
-3.500 0.1691 0.04122 0.03869 -0.1086 0.9074 0.0093
-3.250 0.2254 0.03667 0.03399 -0.1183 0.8959 0.0093
-3.000 0.2804 0.03225 0.02938 -0.1271 0.8785 0.0093
-2.750 0.3074 0.01082 0.00762 -0.1225 0.7906 0.0093
-2.500 0.3658 0.02331 0.01982 -0.1379 0.8285 0.0059
-2.250 0.4024 0.01906 0.01512 -0.1405 0.8049 0.0057
-2.000 0.4368 0.01420 0.00952 -0.1418 0.7858 0.0058
-1.750 0.4659 0.01198 0.00661 -0.1416 0.7675 0.0063
-1.500 0.4924 0.01096 0.00524 -0.1412 0.7508 0.0068
-1.250 0.5184 0.01076 0.00489 -0.1406 0.7352 0.0080
-1.000 0.5449 0.01036 0.00424 -0.1400 0.7207 0.0090
-0.750 0.5714 0.00979 0.00347 -0.1394 0.7073 0.0090
-0.500 0.5978 0.00937 0.00291 -0.1388 0.6946 0.0091
-0.250 0.6242 0.00908 0.00251 -0.1382 0.6825 0.0093
0.000 0.6505 0.00877 0.00211 -0.1377 0.6709 0.0099
0.250 0.6768 0.00864 0.00188 -0.1371 0.6588 0.0115
0.750 0.7288 0.00834 0.00166 -0.1360 0.6324 0.0932
1.000 0.7545 0.00830 0.00169 -0.1354 0.6175 0.1483
1.250 0.7799 0.00827 0.00175 -0.1348 0.6012 0.2204
1.500 0.8052 0.00828 0.00181 -0.1342 0.5828 0.2800
1.750 0.8301 0.00835 0.00188 -0.1335 0.5606 0.3316
2.000 0.8548 0.00843 0.00198 -0.1327 0.5337 0.3970
2.250 0.8784 0.00856 0.00211 -0.1318 0.4985 0.4759
2.500 0.9001 0.00854 0.00224 -0.1307 0.4585 0.6381
2.750 0.9283 0.00836 0.00238 -0.1307 0.4196 1.0000
3.250 0.9756 0.00910 0.00271 -0.1290 0.3511 1.0000
3.500 0.9992 0.00949 0.00291 -0.1282 0.3170 1.0000
3.750 1.0233 0.00982 0.00312 -0.1274 0.2910 1.0000
4.000 1.0475 0.01014 0.00331 -0.1267 0.2687 1.0000
4.250 1.0714 0.01049 0.00353 -0.1259 0.2437 1.0000
4.500 1.0948 0.01089 0.00378 -0.1251 0.2161 1.0000
4.750 1.1181 0.01131 0.00405 -0.1243 0.1895 1.0000
5.000 1.1415 0.01170 0.00435 -0.1234 0.1687 1.0000
5.250 1.1649 0.01208 0.00465 -0.1226 0.1503 1.0000
5.500 1.1882 0.01247 0.00495 -0.1218 0.1340 1.0000
5.750 1.2114 0.01286 0.00527 -0.1210 0.1201 1.0000
6.000 1.2347 0.01323 0.00560 -0.1202 0.1084 1.0000
6.250 1.2579 0.01361 0.00596 -0.1193 0.0984 1.0000
6.500 1.2807 0.01401 0.00632 -0.1184 0.0897 1.0000
6.750 1.3036 0.01440 0.00670 -0.1176 0.0821 1.0000
7.000 1.3263 0.01480 0.00709 -0.1167 0.0757 1.0000
7.250 1.3488 0.01520 0.00750 -0.1158 0.0705 1.0000
7.500 1.3708 0.01565 0.00796 -0.1148 0.0659 1.0000
7.750 1.3933 0.01601 0.00838 -0.1139 0.0634 1.0000
8.000 1.4153 0.01642 0.00883 -0.1129 0.0607 1.0000
8.250 1.4367 0.01689 0.00934 -0.1118 0.0582 1.0000
8.500 1.4572 0.01742 0.00990 -0.1106 0.0556 1.0000
8.750 1.4776 0.01793 0.01048 -0.1094 0.0541 1.0000
9.000 1.4984 0.01838 0.01102 -0.1082 0.0530 1.0000
9.250 1.5185 0.01887 0.01162 -0.1069 0.0519 1.0000
9.500 1.5382 0.01938 0.01222 -0.1056 0.0504 1.0000
9.750 1.5573 0.01992 0.01281 -0.1043 0.0486 1.0000
10.000 1.5755 0.02050 0.01344 -0.1028 0.0464 1.0000
10.250 1.5923 0.02117 0.01415 -0.1011 0.0433 1.0000
10.500 1.6122 0.02153 0.01461 -0.1000 0.0413 1.0000
10.750 1.6299 0.02200 0.01514 -0.0985 0.0381 1.0000
11.000 1.6444 0.02265 0.01578 -0.0965 0.0339 1.0000
11.250 1.6600 0.02317 0.01638 -0.0946 0.0307 1.0000
11.500 1.6727 0.02391 0.01712 -0.0924 0.0257 1.0000
11.750 1.6816 0.02492 0.01810 -0.0898 0.0174 1.0000
12.000 1.6836 0.02649 0.01963 -0.0863 0.0096 1.0000
12.250 1.6856 0.02808 0.02129 -0.0829 0.0052 1.0000
12.500 1.6861 0.02985 0.02316 -0.0797 0.0024 1.0000
12.750 1.6883 0.03153 0.02496 -0.0768 0.0016 1.0000
13.000 1.6911 0.03322 0.02680 -0.0743 0.0013 1.0000
13.250 1.6935 0.03500 0.02876 -0.0720 0.0011 1.0000
13.500 1.6944 0.03701 0.03093 -0.0699 0.0010 1.0000
13.750 1.6946 0.03920 0.03328 -0.0680 0.0009 1.0000
14.000 1.6921 0.04179 0.03605 -0.0664 0.0009 1.0000
14.250 1.6879 0.04472 0.03916 -0.0650 0.0008 1.0000
14.500 1.6827 0.04795 0.04257 -0.0641 0.0008 1.0000
14.750 1.6734 0.05191 0.04673 -0.0637 0.0007 1.0000
15.000 1.6647 0.05602 0.05102 -0.0637 0.0007 1.0000
15.250 1.6558 0.06039 0.05557 -0.0642 0.0007 1.0000
15.500 1.6447 0.06536 0.06071 -0.0653 0.0007 1.0000
15.750 1.6321 0.07082 0.06636 -0.0668 0.0007 1.0000
16.000 1.6164 0.07721 0.07293 -0.0691 0.0007 1.0000
16.250 1.5998 0.08413 0.08004 -0.0721 0.0007 1.0000
16.500 1.5809 0.09197 0.08807 -0.0758 0.0006 1.0000
16.750 1.5583 0.10103 0.09732 -0.0804 0.0007 1.0000
17.000 1.5342 0.11084 0.10732 -0.0857 0.0007 1.0000
17.250 1.5082 0.12144 0.11810 -0.0915 0.0007 1.0000
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