HT12 (ht12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT12 (ht12-il) Reynolds number: 200,000 Max Cl/Cd: 32.3 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht12-il-200000.txt Download as CSV file: xf-ht12-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HT12
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.7449 0.09514 0.09180 0.0366 1.0000 0.0489
-8.000 -0.7447 0.09055 0.08725 0.0332 1.0000 0.0503
-7.750 -0.7421 0.08482 0.08153 0.0265 1.0000 0.0521
-7.500 -0.7332 0.07317 0.06959 0.0054 1.0000 0.0554
-7.250 -0.7318 0.06432 0.06055 0.0006 1.0000 0.0564
-7.000 -0.7186 0.06101 0.05736 0.0019 1.0000 0.0577
-6.750 -0.7038 0.05788 0.05419 0.0016 1.0000 0.0596
-6.500 -0.6873 0.05337 0.04950 -0.0006 1.0000 0.0628
-6.250 -0.6704 0.03742 0.03235 -0.0060 1.0000 0.0404
-6.000 -0.6493 0.03202 0.02638 -0.0066 1.0000 0.0394
-5.750 -0.6256 0.02715 0.02083 -0.0066 1.0000 0.0381
-5.500 -0.5998 0.02324 0.01627 -0.0062 1.0000 0.0373
-5.250 -0.5731 0.02079 0.01340 -0.0057 1.0000 0.0384
-5.000 -0.5458 0.01918 0.01147 -0.0053 1.0000 0.0412
-4.750 -0.5186 0.01756 0.00957 -0.0049 1.0000 0.0445
-4.500 -0.4922 0.01588 0.00784 -0.0045 1.0000 0.0484
-4.250 -0.4649 0.01497 0.00682 -0.0041 1.0000 0.0542
-4.000 -0.4383 0.01380 0.00568 -0.0039 1.0000 0.0630
-3.750 -0.4113 0.01281 0.00471 -0.0036 1.0000 0.0749
-3.500 -0.3841 0.01197 0.00393 -0.0034 1.0000 0.0987
-3.250 -0.3571 0.01105 0.00329 -0.0033 1.0000 0.1508
-3.000 -0.3304 0.01025 0.00293 -0.0033 1.0000 0.2412
-2.750 -0.3035 0.00971 0.00270 -0.0033 1.0000 0.3247
-2.500 -0.2768 0.00924 0.00251 -0.0031 1.0000 0.3998
-2.250 -0.2505 0.00873 0.00229 -0.0027 1.0000 0.4816
-2.000 -0.2262 0.00801 0.00214 -0.0019 1.0000 0.6033
-1.750 -0.2093 0.00713 0.00210 0.0015 1.0000 0.8148
-1.500 -0.1625 0.00683 0.00194 -0.0015 1.0000 1.0000
-1.250 -0.1355 0.00680 0.00178 -0.0012 1.0000 1.0000
-1.000 -0.1084 0.00677 0.00167 -0.0010 1.0000 1.0000
-0.750 -0.0813 0.00674 0.00158 -0.0007 1.0000 1.0000
-0.500 -0.0542 0.00673 0.00152 -0.0005 1.0000 1.0000
-0.250 -0.0271 0.00672 0.00148 -0.0002 1.0000 1.0000
0.000 0.0001 0.00672 0.00147 0.0000 1.0000 1.0000
0.250 0.0272 0.00672 0.00148 0.0002 1.0000 1.0000
0.500 0.0544 0.00673 0.00152 0.0005 1.0000 1.0000
0.750 0.0815 0.00674 0.00158 0.0007 1.0000 1.0000
1.000 0.1086 0.00677 0.00167 0.0010 1.0000 1.0000
1.250 0.1356 0.00680 0.00178 0.0012 1.0000 1.0000
1.500 0.1627 0.00683 0.00194 0.0015 1.0000 1.0000
1.750 0.2094 0.00714 0.00210 -0.0015 0.8133 1.0000
2.000 0.2263 0.00802 0.00214 0.0019 0.6024 1.0000
2.250 0.2507 0.00873 0.00230 0.0027 0.4813 1.0000
2.500 0.2770 0.00924 0.00251 0.0031 0.3992 1.0000
2.750 0.3037 0.00972 0.00271 0.0033 0.3242 1.0000
3.000 0.3305 0.01026 0.00293 0.0033 0.2406 1.0000
3.250 0.3572 0.01106 0.00329 0.0033 0.1505 1.0000
3.500 0.3843 0.01197 0.00393 0.0034 0.0986 1.0000
3.750 0.4115 0.01282 0.00472 0.0036 0.0749 1.0000
4.000 0.4385 0.01380 0.00569 0.0039 0.0629 1.0000
4.250 0.4651 0.01497 0.00682 0.0041 0.0541 1.0000
4.500 0.4924 0.01589 0.00785 0.0045 0.0483 1.0000
4.750 0.5189 0.01755 0.00956 0.0049 0.0444 1.0000
5.000 0.5460 0.01920 0.01150 0.0053 0.0412 1.0000
5.250 0.5733 0.02082 0.01342 0.0057 0.0384 1.0000
5.500 0.6000 0.02327 0.01630 0.0062 0.0373 1.0000
5.750 0.6258 0.02718 0.02087 0.0065 0.0381 1.0000
6.000 0.6495 0.03206 0.02643 0.0065 0.0394 1.0000
6.250 0.6707 0.03744 0.03238 0.0060 0.0404 1.0000
6.500 0.6875 0.05341 0.04955 0.0005 0.0628 1.0000
6.750 0.7041 0.05796 0.05427 -0.0017 0.0595 1.0000
7.000 0.7189 0.06109 0.05743 -0.0020 0.0576 1.0000
7.250 0.7320 0.06437 0.06060 -0.0007 0.0563 1.0000
7.500 0.7335 0.07321 0.06964 -0.0054 0.0553 1.0000
7.750 0.7425 0.08486 0.08158 -0.0265 0.0521 1.0000
8.000 0.7451 0.09063 0.08733 -0.0333 0.0503 1.0000
8.250 0.7454 0.09522 0.09188 -0.0368 0.0488 1.0000
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Polar data table (+)
Polar graphs
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