HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 200,000 Max Cl/Cd: 90.73 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1606-il-200000-n5.txt Download as CSV file: xf-hs1606-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-606 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3551 0.10437 0.10081 -0.0329 1.0000 0.0215
-8.500 -0.3547 0.10182 0.09832 -0.0331 1.0000 0.0216
-8.250 -0.3567 0.09951 0.09607 -0.0325 1.0000 0.0217
-7.250 -0.3319 0.08405 0.08070 -0.0378 0.9878 0.0126
-7.000 -0.3100 0.07912 0.07576 -0.0447 0.9832 0.0116
-6.750 -0.2886 0.07362 0.07025 -0.0523 0.9755 0.0106
-6.500 -0.2567 0.06489 0.06147 -0.0650 0.9702 0.0091
-6.250 -0.2290 0.05967 0.05618 -0.0724 0.9630 0.0088
-6.000 -0.1945 0.05292 0.04933 -0.0827 0.9583 0.0087
-5.750 -0.1552 0.04469 0.04092 -0.0942 0.9528 0.0086
-5.500 -0.0986 0.02765 0.02299 -0.1127 0.9483 0.0083
-5.250 -0.0589 0.02236 0.01677 -0.1179 0.9454 0.0088
-5.000 -0.0243 0.01953 0.01348 -0.1208 0.9431 0.0105
-4.750 0.0062 0.01793 0.01151 -0.1219 0.9385 0.0115
-4.500 0.0382 0.01640 0.00962 -0.1229 0.9348 0.0117
-4.250 0.0707 0.01526 0.00821 -0.1239 0.9317 0.0120
-4.000 0.1027 0.01440 0.00709 -0.1248 0.9285 0.0125
-3.750 0.1322 0.01378 0.00626 -0.1251 0.9236 0.0132
-3.500 0.1630 0.01324 0.00553 -0.1256 0.9200 0.0143
-3.250 0.1943 0.01260 0.00477 -0.1262 0.9172 0.0202
-3.000 0.2231 0.01208 0.00444 -0.1265 0.9128 0.0694
-2.750 0.2519 0.01196 0.00441 -0.1269 0.9086 0.1075
-2.500 0.2815 0.01182 0.00422 -0.1272 0.9055 0.1219
-2.250 0.3107 0.01169 0.00406 -0.1274 0.9020 0.1340
-2.000 0.3386 0.01163 0.00398 -0.1274 0.8973 0.1479
-1.750 0.3674 0.01156 0.00388 -0.1276 0.8935 0.1618
-1.500 0.3965 0.01147 0.00376 -0.1277 0.8900 0.1735
-1.250 0.4235 0.01143 0.00371 -0.1275 0.8830 0.1851
-1.000 0.4518 0.01133 0.00359 -0.1274 0.8770 0.1972
-0.750 0.4787 0.01127 0.00352 -0.1270 0.8691 0.2084
-0.500 0.5067 0.01118 0.00341 -0.1268 0.8625 0.2204
0.000 0.5609 0.01103 0.00331 -0.1262 0.8460 0.2457
0.250 0.5879 0.01095 0.00327 -0.1259 0.8372 0.2598
0.500 0.6153 0.01087 0.00327 -0.1257 0.8295 0.2771
0.750 0.6429 0.01076 0.00328 -0.1256 0.8231 0.3072
1.000 0.6611 0.00943 0.00339 -0.1233 0.8166 0.8701
1.250 0.6900 0.00940 0.00338 -0.1234 0.8092 1.0000
1.500 0.7173 0.00947 0.00342 -0.1231 0.8010 1.0000
1.750 0.7448 0.00954 0.00345 -0.1228 0.7929 1.0000
2.000 0.7717 0.00961 0.00354 -0.1225 0.7826 1.0000
2.250 0.7987 0.00969 0.00362 -0.1222 0.7717 1.0000
2.500 0.8255 0.00976 0.00374 -0.1218 0.7590 1.0000
2.750 0.8520 0.00983 0.00383 -0.1213 0.7439 1.0000
3.000 0.8784 0.00990 0.00392 -0.1208 0.7261 1.0000
3.250 0.9040 0.00998 0.00397 -0.1200 0.6966 1.0000
3.500 0.9264 0.01021 0.00391 -0.1183 0.6159 1.0000
3.750 0.9441 0.01105 0.00411 -0.1161 0.5123 1.0000
4.000 0.9632 0.01191 0.00454 -0.1145 0.4306 1.0000
4.250 0.9826 0.01277 0.00503 -0.1131 0.3597 1.0000
4.500 1.0027 0.01361 0.00554 -0.1119 0.2964 1.0000
4.750 1.0236 0.01439 0.00608 -0.1109 0.2362 1.0000
5.000 1.0423 0.01546 0.00672 -0.1096 0.1537 1.0000
5.250 1.0591 0.01685 0.00761 -0.1081 0.0744 1.0000
5.500 1.0801 0.01769 0.00838 -0.1071 0.0555 1.0000
5.750 1.1020 0.01841 0.00913 -0.1061 0.0468 1.0000
6.000 1.1234 0.01915 0.00994 -0.1050 0.0417 1.0000
6.250 1.1433 0.02007 0.01097 -0.1037 0.0382 1.0000
6.500 1.1640 0.02084 0.01188 -0.1025 0.0361 1.0000
6.750 1.1838 0.02169 0.01285 -0.1012 0.0337 1.0000
7.000 1.2033 0.02255 0.01378 -0.0999 0.0310 1.0000
7.250 1.2196 0.02379 0.01507 -0.0982 0.0286 1.0000
7.500 1.2358 0.02519 0.01657 -0.0964 0.0274 1.0000
7.750 1.2545 0.02629 0.01782 -0.0949 0.0264 1.0000
8.000 1.2730 0.02757 0.01930 -0.0934 0.0253 1.0000
8.250 1.2917 0.02887 0.02077 -0.0919 0.0238 1.0000
8.500 1.3098 0.02993 0.02197 -0.0906 0.0219 1.0000
8.750 1.3266 0.03114 0.02330 -0.0891 0.0204 1.0000
9.000 1.3406 0.03353 0.02580 -0.0874 0.0185 1.0000
9.250 1.3570 0.03395 0.02649 -0.0857 0.0167 1.0000
9.500 1.3713 0.03476 0.02750 -0.0839 0.0145 1.0000
9.750 1.3823 0.03545 0.02830 -0.0817 0.0130 1.0000
10.000 1.3880 0.03689 0.02985 -0.0789 0.0118 1.0000
10.250 1.3964 0.03886 0.03215 -0.0763 0.0103 1.0000
10.500 1.4045 0.04015 0.03372 -0.0739 0.0088 1.0000
10.750 1.4131 0.04073 0.03437 -0.0719 0.0077 1.0000
11.000 1.4164 0.04226 0.03601 -0.0697 0.0070 1.0000
11.250 1.4148 0.04532 0.03941 -0.0668 0.0065 1.0000
11.500 1.4095 0.04875 0.04321 -0.0639 0.0061 1.0000
11.750 1.4011 0.05246 0.04727 -0.0613 0.0057 1.0000
12.000 1.3900 0.05646 0.05159 -0.0592 0.0055 1.0000
12.250 1.3765 0.06085 0.05628 -0.0577 0.0054 1.0000
12.500 1.3608 0.06570 0.06142 -0.0569 0.0052 1.0000
12.750 1.3423 0.07125 0.06724 -0.0569 0.0052 1.0000
13.000 1.3212 0.07766 0.07392 -0.0582 0.0052 1.0000
13.250 1.2977 0.08516 0.08168 -0.0608 0.0052 1.0000
13.500 1.2729 0.09389 0.09064 -0.0651 0.0053 1.0000
13.750 1.2476 0.10399 0.10096 -0.0712 0.0054 1.0000
14.000 1.2221 0.11545 0.11259 -0.0785 0.0057 1.0000
14.250 1.1971 0.12799 0.12525 -0.0865 0.0060 1.0000
14.500 1.1739 0.14074 0.13806 -0.0940 0.0064 1.0000
14.750 1.1503 0.15420 0.15147 -0.1012 0.0068 1.0000
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Polar data table (+)
Polar graphs
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