HT05 (ht05-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT05 (ht05-il) Reynolds number: 200,000 Max Cl/Cd: 31.11 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht05-il-200000.txt Download as CSV file: xf-ht05-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HT05
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7217 0.11398 0.11046 0.0325 1.0000 0.0461
-9.250 -0.7253 0.10937 0.10590 0.0262 1.0000 0.0471
-9.000 -0.7274 0.10460 0.10119 0.0211 1.0000 0.0473
-8.750 -0.7288 0.09955 0.09617 0.0160 1.0000 0.0475
-8.500 -0.7280 0.09362 0.09023 0.0096 1.0000 0.0475
-8.250 -0.7329 0.08757 0.08422 0.0125 1.0000 0.0488
-8.000 -0.7259 0.08458 0.08122 0.0138 1.0000 0.0499
-7.750 -0.7188 0.08082 0.07746 0.0124 1.0000 0.0512
-7.500 -0.7112 0.07616 0.07277 0.0090 1.0000 0.0529
-7.250 -0.7022 0.07040 0.06693 0.0039 1.0000 0.0553
-7.000 -0.6900 0.06201 0.05784 -0.0074 1.0000 0.0602
-6.750 -0.6360 0.04390 0.04030 -0.0090 1.0000 0.0628
-6.250 -0.6575 0.03452 0.02877 -0.0092 1.0000 0.0363
-6.000 -0.6401 0.02956 0.02332 -0.0088 1.0000 0.0373
-5.750 -0.6174 0.02617 0.01938 -0.0079 1.0000 0.0368
-5.500 -0.5940 0.02304 0.01577 -0.0071 1.0000 0.0371
-5.250 -0.5696 0.02063 0.01308 -0.0064 1.0000 0.0385
-5.000 -0.5442 0.01922 0.01150 -0.0058 1.0000 0.0414
-4.750 -0.5180 0.01817 0.01020 -0.0052 1.0000 0.0457
-4.500 -0.4921 0.01654 0.00834 -0.0044 1.0000 0.0485
-4.250 -0.4670 0.01517 0.00699 -0.0037 1.0000 0.0540
-4.000 -0.4413 0.01425 0.00600 -0.0031 1.0000 0.0625
-3.750 -0.4154 0.01347 0.00520 -0.0025 1.0000 0.0730
-3.500 -0.3903 0.01255 0.00438 -0.0019 1.0000 0.0920
-3.250 -0.3647 0.01181 0.00378 -0.0014 1.0000 0.1242
-3.000 -0.3393 0.01113 0.00337 -0.0009 1.0000 0.1768
-2.750 -0.3139 0.01056 0.00306 -0.0005 1.0000 0.2387
-2.500 -0.2890 0.00995 0.00281 0.0000 1.0000 0.3173
-2.250 -0.2656 0.00921 0.00262 0.0008 1.0000 0.4453
-2.000 -0.2422 0.00876 0.00262 0.0019 1.0000 0.5852
-1.750 -0.2178 0.00833 0.00233 0.0028 1.0000 0.6495
-1.500 -0.1552 0.00750 0.00246 -0.0031 1.0000 0.9919
-1.250 -0.1214 0.00748 0.00233 -0.0043 1.0000 1.0000
-1.000 -0.0969 0.00744 0.00222 -0.0035 1.0000 1.0000
-0.750 -0.0725 0.00742 0.00214 -0.0027 1.0000 1.0000
-0.500 -0.0483 0.00740 0.00208 -0.0018 1.0000 1.0000
-0.250 -0.0241 0.00739 0.00204 -0.0009 1.0000 1.0000
0.000 0.0001 0.00739 0.00203 0.0000 1.0000 1.0000
0.250 0.0242 0.00739 0.00204 0.0009 1.0000 1.0000
0.500 0.0484 0.00740 0.00208 0.0018 1.0000 1.0000
0.750 0.0726 0.00742 0.00214 0.0027 1.0000 1.0000
1.000 0.0970 0.00744 0.00222 0.0035 1.0000 1.0000
1.250 0.1215 0.00748 0.00233 0.0043 1.0000 1.0000
1.500 0.1558 0.00750 0.00246 0.0030 0.9913 1.0000
1.750 0.2179 0.00833 0.00233 -0.0028 0.6493 1.0000
2.000 0.2424 0.00876 0.00262 -0.0019 0.5850 1.0000
2.250 0.2657 0.00922 0.00262 -0.0008 0.4446 1.0000
2.500 0.2891 0.00995 0.00281 0.0000 0.3166 1.0000
2.750 0.3140 0.01056 0.00306 0.0005 0.2382 1.0000
3.000 0.3394 0.01113 0.00337 0.0009 0.1765 1.0000
3.250 0.3648 0.01181 0.00378 0.0014 0.1242 1.0000
3.500 0.3904 0.01255 0.00438 0.0019 0.0919 1.0000
3.750 0.4156 0.01347 0.00520 0.0025 0.0730 1.0000
4.000 0.4414 0.01427 0.00602 0.0031 0.0624 1.0000
4.250 0.4672 0.01516 0.00698 0.0037 0.0539 1.0000
4.500 0.4921 0.01665 0.00845 0.0044 0.0484 1.0000
4.750 0.5182 0.01816 0.01020 0.0052 0.0457 1.0000
5.000 0.5443 0.01920 0.01147 0.0058 0.0414 1.0000
5.250 0.5697 0.02063 0.01308 0.0064 0.0385 1.0000
5.500 0.5940 0.02311 0.01585 0.0071 0.0371 1.0000
5.750 0.6175 0.02629 0.01951 0.0079 0.0369 1.0000
6.000 0.6400 0.02963 0.02338 0.0088 0.0372 1.0000
6.250 0.6570 0.03485 0.02912 0.0092 0.0363 1.0000
6.750 0.6843 0.05435 0.05025 0.0082 0.0620 1.0000
7.000 0.6902 0.06206 0.05789 0.0073 0.0604 1.0000
7.250 0.7025 0.07047 0.06700 -0.0040 0.0553 1.0000
7.500 0.7115 0.07615 0.07276 -0.0090 0.0530 1.0000
7.750 0.7192 0.08074 0.07737 -0.0123 0.0513 1.0000
8.000 0.7265 0.08444 0.08108 -0.0135 0.0500 1.0000
8.250 0.7334 0.08740 0.08406 -0.0119 0.0489 1.0000
8.500 0.7283 0.09374 0.09035 -0.0098 0.0477 1.0000
8.750 0.7291 0.09964 0.09627 -0.0163 0.0476 1.0000
9.000 0.7278 0.10468 0.10126 -0.0215 0.0475 1.0000
9.250 0.7255 0.10947 0.10599 -0.0267 0.0472 1.0000
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Polar data table (+)
Polar graphs
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