HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il) Reynolds number: 200,000 Max Cl/Cd: 92.76 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1708-il-200000-n5.txt Download as CSV file: xf-hs1708-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-708 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3267 0.11824 0.11454 -0.0395 1.0000 0.0194
-10.250 -0.3234 0.11595 0.11228 -0.0386 1.0000 0.0186
-10.000 -0.3248 0.11356 0.10995 -0.0377 1.0000 0.0178
-9.500 -0.3173 0.10261 0.09903 -0.0452 0.9933 0.0149
-9.250 -0.3048 0.09867 0.09509 -0.0486 0.9887 0.0148
-9.000 -0.2915 0.09448 0.09089 -0.0526 0.9849 0.0147
-8.750 -0.2810 0.09033 0.08673 -0.0562 0.9778 0.0146
-8.500 -0.2688 0.08581 0.08222 -0.0608 0.9723 0.0145
-8.250 -0.2608 0.08157 0.07799 -0.0644 0.9627 0.0145
-8.000 -0.2500 0.07674 0.07315 -0.0695 0.9549 0.0145
-7.750 -0.2369 0.07105 0.06745 -0.0764 0.9470 0.0145
-7.250 -0.1870 0.02405 0.01862 -0.1339 0.9269 0.0148
-7.000 -0.1576 0.02192 0.01615 -0.1359 0.9224 0.0159
-6.750 -0.1273 0.02061 0.01460 -0.1373 0.9190 0.0175
-6.500 -0.0959 0.01898 0.01255 -0.1388 0.9164 0.0195
-6.250 -0.0670 0.01788 0.01126 -0.1396 0.9124 0.0218
-6.000 -0.0378 0.01698 0.01012 -0.1402 0.9085 0.0257
-5.750 -0.0082 0.01642 0.00946 -0.1409 0.9052 0.0304
-5.500 0.0219 0.01583 0.00869 -0.1415 0.9024 0.0353
-5.250 0.0506 0.01561 0.00836 -0.1418 0.8987 0.0407
-5.000 0.0789 0.01540 0.00808 -0.1420 0.8949 0.0470
-4.750 0.1078 0.01522 0.00778 -0.1423 0.8917 0.0530
-4.500 0.1371 0.01480 0.00726 -0.1427 0.8890 0.0580
-4.000 0.1947 0.01417 0.00639 -0.1431 0.8826 0.0671
-3.750 0.2231 0.01386 0.00608 -0.1434 0.8792 0.0728
-3.500 0.2520 0.01363 0.00577 -0.1436 0.8764 0.0788
-3.250 0.2811 0.01338 0.00549 -0.1439 0.8739 0.0854
-3.000 0.3102 0.01322 0.00526 -0.1441 0.8714 0.0933
-2.750 0.3380 0.01307 0.00514 -0.1442 0.8677 0.1008
-2.500 0.3664 0.01296 0.00502 -0.1443 0.8645 0.1107
-2.250 0.3951 0.01287 0.00490 -0.1444 0.8615 0.1217
-2.000 0.4241 0.01275 0.00479 -0.1446 0.8585 0.1322
-1.750 0.4516 0.01269 0.00475 -0.1445 0.8534 0.1437
-1.500 0.4793 0.01262 0.00467 -0.1443 0.8476 0.1560
-1.250 0.5081 0.01252 0.00452 -0.1442 0.8428 0.1676
-1.000 0.5349 0.01248 0.00451 -0.1440 0.8360 0.1792
-0.750 0.5632 0.01238 0.00441 -0.1438 0.8302 0.1908
-0.500 0.5906 0.01233 0.00438 -0.1437 0.8240 0.2020
-0.250 0.6184 0.01226 0.00433 -0.1435 0.8176 0.2141
0.000 0.6461 0.01219 0.00428 -0.1433 0.8111 0.2271
0.250 0.6735 0.01213 0.00426 -0.1431 0.8040 0.2405
0.500 0.7017 0.01205 0.00423 -0.1431 0.7988 0.2560
0.750 0.7289 0.01200 0.00429 -0.1429 0.7923 0.2751
1.000 0.7570 0.01189 0.00428 -0.1429 0.7866 0.3044
1.250 0.7831 0.01129 0.00444 -0.1428 0.7799 0.5659
1.750 0.8306 0.01059 0.00440 -0.1403 0.7647 1.0000
2.000 0.8583 0.01063 0.00439 -0.1400 0.7564 1.0000
2.250 0.8849 0.01070 0.00447 -0.1396 0.7457 1.0000
2.500 0.9118 0.01077 0.00453 -0.1393 0.7350 1.0000
2.750 0.9386 0.01083 0.00460 -0.1389 0.7229 1.0000
3.000 0.9650 0.01089 0.00466 -0.1384 0.7074 1.0000
3.250 0.9909 0.01096 0.00470 -0.1378 0.6866 1.0000
3.500 1.0164 0.01104 0.00474 -0.1371 0.6571 1.0000
3.750 1.0408 0.01122 0.00473 -0.1361 0.6159 1.0000
4.000 1.0632 0.01158 0.00483 -0.1347 0.5704 1.0000
4.250 1.0846 0.01209 0.00512 -0.1334 0.5290 1.0000
4.500 1.1043 0.01272 0.00549 -0.1318 0.4823 1.0000
4.750 1.1227 0.01344 0.00593 -0.1300 0.4315 1.0000
5.000 1.1407 0.01417 0.00642 -0.1283 0.3870 1.0000
5.250 1.1595 0.01485 0.00690 -0.1268 0.3522 1.0000
5.500 1.1794 0.01546 0.00738 -0.1255 0.3245 1.0000
5.750 1.1998 0.01602 0.00786 -0.1242 0.3017 1.0000
6.000 1.2208 0.01653 0.00834 -0.1231 0.2794 1.0000
6.250 1.2409 0.01708 0.00883 -0.1218 0.2555 1.0000
6.500 1.2595 0.01773 0.00936 -0.1203 0.2243 1.0000
6.750 1.2760 0.01854 0.00998 -0.1186 0.1868 1.0000
7.000 1.2907 0.01950 0.01072 -0.1166 0.1463 1.0000
7.250 1.3039 0.02057 0.01158 -0.1144 0.1076 1.0000
7.500 1.3174 0.02160 0.01247 -0.1122 0.0834 1.0000
7.750 1.3310 0.02253 0.01335 -0.1099 0.0706 1.0000
8.000 1.3445 0.02335 0.01420 -0.1076 0.0629 1.0000
8.250 1.3561 0.02435 0.01519 -0.1051 0.0569 1.0000
8.500 1.3705 0.02515 0.01612 -0.1031 0.0533 1.0000
8.750 1.3834 0.02607 0.01713 -0.1009 0.0500 1.0000
9.000 1.3941 0.02718 0.01828 -0.0985 0.0470 1.0000
9.250 1.4040 0.02836 0.01954 -0.0961 0.0445 1.0000
9.500 1.4165 0.02936 0.02066 -0.0941 0.0423 1.0000
9.750 1.4277 0.03048 0.02189 -0.0920 0.0402 1.0000
10.000 1.4376 0.03172 0.02323 -0.0899 0.0385 1.0000
10.250 1.4456 0.03315 0.02475 -0.0877 0.0370 1.0000
10.500 1.4502 0.03492 0.02659 -0.0852 0.0355 1.0000
10.750 1.4580 0.03647 0.02826 -0.0831 0.0344 1.0000
11.000 1.4676 0.03787 0.02981 -0.0812 0.0332 1.0000
11.250 1.4763 0.03937 0.03145 -0.0794 0.0318 1.0000
11.500 1.4839 0.04099 0.03319 -0.0776 0.0305 1.0000
11.750 1.4904 0.04274 0.03506 -0.0758 0.0295 1.0000
12.000 1.4961 0.04459 0.03702 -0.0741 0.0285 1.0000
12.250 1.5002 0.04662 0.03915 -0.0724 0.0276 1.0000
12.500 1.5014 0.04905 0.04168 -0.0705 0.0266 1.0000
12.750 1.5051 0.05127 0.04406 -0.0689 0.0258 1.0000
13.000 1.5097 0.05339 0.04637 -0.0675 0.0249 1.0000
13.250 1.5126 0.05569 0.04887 -0.0662 0.0240 1.0000
13.500 1.5143 0.05818 0.05153 -0.0649 0.0231 1.0000
13.750 1.5149 0.06079 0.05430 -0.0639 0.0222 1.0000
14.000 1.5147 0.06354 0.05719 -0.0632 0.0214 1.0000
14.250 1.5133 0.06650 0.06028 -0.0626 0.0207 1.0000
14.500 1.5101 0.06982 0.06371 -0.0623 0.0200 1.0000
14.750 1.5042 0.07364 0.06764 -0.0620 0.0194 1.0000
15.000 1.4988 0.07760 0.07179 -0.0620 0.0188 1.0000
15.250 1.4936 0.08172 0.07616 -0.0625 0.0183 1.0000
15.500 1.4871 0.08619 0.08088 -0.0632 0.0177 1.0000
15.750 1.4797 0.09098 0.08588 -0.0644 0.0171 1.0000
16.000 1.4716 0.09607 0.09117 -0.0660 0.0165 1.0000
16.250 1.4628 0.10145 0.09673 -0.0680 0.0160 1.0000
16.500 1.4534 0.10710 0.10256 -0.0704 0.0156 1.0000
16.750 1.4435 0.11301 0.10863 -0.0731 0.0153 1.0000
17.000 1.4333 0.11914 0.11491 -0.0762 0.0149 1.0000
17.250 1.4226 0.12558 0.12150 -0.0796 0.0147 1.0000
17.500 1.4117 0.13223 0.12828 -0.0834 0.0144 1.0000
17.750 1.3998 0.13926 0.13545 -0.0875 0.0142 1.0000
18.000 1.3869 0.14665 0.14299 -0.0920 0.0140 1.0000
18.250 1.3730 0.15451 0.15098 -0.0969 0.0138 1.0000
18.500 1.3577 0.16309 0.15971 -0.1025 0.0137 1.0000
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