HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 200,000 Max Cl/Cd: 95.44 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1606-il-200000.txt Download as CSV file: xf-hs1606-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3795 0.09487 0.09166 -0.0234 1.0000 0.0337
-7.250 -0.3951 0.09416 0.09103 -0.0194 1.0000 0.0339
-7.000 -0.4051 0.09287 0.08980 -0.0169 1.0000 0.0344
-6.750 -0.4120 0.09124 0.08822 -0.0152 1.0000 0.0350
-6.500 -0.3955 0.08752 0.08449 -0.0196 0.9973 0.0364
-6.250 -0.3694 0.08293 0.07988 -0.0272 0.9938 0.0387
-6.000 -0.3203 0.07731 0.07417 -0.0464 0.9877 0.0425
-5.750 -0.2764 0.07162 0.06836 -0.0589 0.9844 0.0429
-5.500 -0.2678 0.06580 0.06260 -0.0589 0.9821 0.0444
-5.250 -0.2474 0.06252 0.05929 -0.0608 0.9778 0.0459
-5.000 -0.2156 0.05844 0.05514 -0.0665 0.9746 0.0483
-4.750 -0.1441 0.05131 0.04761 -0.0843 0.9721 0.0551
-4.500 -0.1009 0.03791 0.03389 -0.0941 0.9711 0.0299
-4.250 -0.0467 0.02731 0.02241 -0.1043 0.9708 0.0283
-4.000 -0.0005 0.02126 0.01519 -0.1093 0.9708 0.0262
-3.750 0.0399 0.01866 0.01193 -0.1118 0.9703 0.0256
-3.500 0.0735 0.01730 0.01029 -0.1129 0.9681 0.0262
-3.250 0.1059 0.01641 0.00922 -0.1138 0.9654 0.0280
-3.000 0.1415 0.01563 0.00827 -0.1153 0.9631 0.0336
-2.750 0.1778 0.01506 0.00787 -0.1170 0.9610 0.0984
-2.500 0.2123 0.01566 0.00842 -0.1187 0.9581 0.1299
-2.250 0.2470 0.01583 0.00848 -0.1202 0.9551 0.1490
-2.000 0.2769 0.01565 0.00826 -0.1207 0.9496 0.1629
-1.750 0.3149 0.01535 0.00797 -0.1228 0.9465 0.1803
-1.500 0.3542 0.01515 0.00776 -0.1253 0.9443 0.2003
-1.250 0.3945 0.01493 0.00748 -0.1279 0.9428 0.2192
-1.000 0.4181 0.01490 0.00750 -0.1272 0.9361 0.2334
-0.750 0.4579 0.01450 0.00717 -0.1296 0.9327 0.2515
-0.500 0.5008 0.01397 0.00670 -0.1324 0.9297 0.2715
-0.250 0.5288 0.01372 0.00654 -0.1323 0.9216 0.2893
0.000 0.5672 0.01315 0.00611 -0.1340 0.9173 0.3144
0.250 0.5944 0.01287 0.00604 -0.1338 0.9095 0.3495
0.500 0.6200 0.01129 0.00589 -0.1327 0.9052 1.0000
0.750 0.6473 0.01138 0.00588 -0.1323 0.8986 1.0000
1.000 0.6768 0.01134 0.00579 -0.1323 0.8927 1.0000
1.250 0.7046 0.01136 0.00580 -0.1319 0.8861 1.0000
1.500 0.7327 0.01132 0.00574 -0.1315 0.8789 1.0000
1.750 0.7595 0.01133 0.00575 -0.1309 0.8709 1.0000
2.000 0.7877 0.01125 0.00567 -0.1305 0.8635 1.0000
2.250 0.8133 0.01127 0.00571 -0.1296 0.8535 1.0000
2.500 0.8398 0.01121 0.00572 -0.1288 0.8437 1.0000
2.750 0.8671 0.01111 0.00563 -0.1280 0.8338 1.0000
3.000 0.8928 0.01106 0.00563 -0.1270 0.8216 1.0000
3.250 0.9179 0.01093 0.00552 -0.1256 0.8050 1.0000
3.500 0.9418 0.01069 0.00531 -0.1238 0.7800 1.0000
3.750 0.9655 0.01054 0.00516 -0.1221 0.7494 1.0000
4.000 0.9892 0.01048 0.00508 -0.1206 0.7100 1.0000
4.250 1.0107 0.01059 0.00493 -0.1185 0.6295 1.0000
4.500 1.0275 0.01142 0.00510 -0.1159 0.5215 1.0000
4.750 1.0452 0.01236 0.00565 -0.1140 0.4375 1.0000
5.000 1.0622 0.01340 0.00627 -0.1121 0.3568 1.0000
5.250 1.0745 0.01501 0.00712 -0.1097 0.2163 1.0000
5.500 1.0829 0.01747 0.00856 -0.1069 0.0813 1.0000
5.750 1.1018 0.01859 0.00967 -0.1053 0.0679 1.0000
6.000 1.1194 0.01984 0.01095 -0.1035 0.0615 1.0000
6.250 1.1387 0.02089 0.01213 -0.1019 0.0571 1.0000
6.500 1.1564 0.02223 0.01347 -0.1002 0.0533 1.0000
6.750 1.1748 0.02394 0.01521 -0.0986 0.0498 1.0000
7.000 1.1969 0.02513 0.01652 -0.0974 0.0472 1.0000
7.250 1.2199 0.02663 0.01813 -0.0964 0.0451 1.0000
7.500 1.2436 0.02831 0.01993 -0.0956 0.0432 1.0000
7.750 1.2677 0.03037 0.02208 -0.0950 0.0412 1.0000
8.000 1.2914 0.03424 0.02625 -0.0945 0.0384 1.0000
8.250 1.3116 0.03610 0.02848 -0.0928 0.0371 1.0000
8.500 1.3288 0.03762 0.03034 -0.0909 0.0338 1.0000
8.750 1.3443 0.03894 0.03173 -0.0895 0.0301 1.0000
9.000 1.3510 0.04300 0.03620 -0.0869 0.0267 1.0000
9.250 1.3586 0.04571 0.03943 -0.0835 0.0243 1.0000
9.500 1.3636 0.04851 0.04258 -0.0804 0.0220 1.0000
9.750 1.2823 0.04432 0.03908 -0.0650 0.0226 1.0000
10.250 1.3480 0.05727 0.05210 -0.0698 0.0175 1.0000
10.500 1.3324 0.06051 0.05566 -0.0650 0.0171 1.0000
10.750 1.3137 0.06429 0.05974 -0.0610 0.0169 1.0000
11.000 1.2935 0.06846 0.06418 -0.0580 0.0169 1.0000
11.250 1.2728 0.07304 0.06899 -0.0562 0.0170 1.0000
11.500 1.2511 0.07810 0.07427 -0.0555 0.0170 1.0000
11.750 1.2290 0.08370 0.08007 -0.0560 0.0171 1.0000
12.000 1.2070 0.08990 0.08644 -0.0578 0.0173 1.0000
12.250 1.1852 0.09684 0.09353 -0.0609 0.0176 1.0000
12.500 1.1637 0.10474 0.10156 -0.0654 0.0179 1.0000
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Polar data table (+)
Polar graphs
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