HT12 (ht12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT12 (ht12-il) Reynolds number: 100,000 Max Cl/Cd: 26.8 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht12-il-100000-n5.txt Download as CSV file: xf-ht12-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7519 0.09840 0.09358 0.0363 1.0000 0.0271
-8.500 -0.7534 0.09321 0.08844 0.0329 1.0000 0.0273
-8.250 -0.7555 0.08766 0.08295 0.0286 1.0000 0.0273
-8.000 -0.7550 0.08098 0.07628 0.0219 1.0000 0.0272
-7.750 -0.7513 0.07294 0.06820 0.0139 1.0000 0.0269
-7.500 -0.7459 0.06366 0.05875 0.0060 1.0000 0.0266
-7.250 -0.7387 0.05460 0.04934 0.0002 1.0000 0.0262
-7.000 -0.7280 0.04652 0.04071 -0.0036 1.0000 0.0260
-6.750 -0.7122 0.04028 0.03384 -0.0055 1.0000 0.0261
-6.500 -0.6925 0.03547 0.02838 -0.0063 1.0000 0.0267
-6.250 -0.6701 0.03159 0.02389 -0.0066 1.0000 0.0276
-6.000 -0.6458 0.02869 0.02042 -0.0065 1.0000 0.0297
-5.750 -0.6198 0.02651 0.01758 -0.0062 1.0000 0.0322
-5.500 -0.5950 0.02387 0.01471 -0.0060 1.0000 0.0341
-5.250 -0.5692 0.02219 0.01285 -0.0057 1.0000 0.0364
-5.000 -0.5428 0.02087 0.01131 -0.0054 1.0000 0.0406
-4.750 -0.5166 0.01949 0.00977 -0.0050 1.0000 0.0453
-4.500 -0.4905 0.01832 0.00851 -0.0047 1.0000 0.0502
-4.250 -0.4641 0.01732 0.00743 -0.0044 1.0000 0.0587
-4.000 -0.4374 0.01642 0.00647 -0.0041 1.0000 0.0696
-3.750 -0.4108 0.01555 0.00566 -0.0039 1.0000 0.0873
-3.500 -0.3840 0.01473 0.00491 -0.0038 1.0000 0.1155
-3.250 -0.3574 0.01397 0.00437 -0.0037 1.0000 0.1647
-3.000 -0.3310 0.01330 0.00398 -0.0035 1.0000 0.2309
-2.750 -0.3045 0.01275 0.00368 -0.0033 1.0000 0.3014
-2.500 -0.2782 0.01224 0.00342 -0.0030 1.0000 0.3697
-2.250 -0.2521 0.01174 0.00314 -0.0026 1.0000 0.4411
-2.000 -0.2267 0.01117 0.00292 -0.0019 1.0000 0.5275
-1.750 -0.2043 0.01045 0.00277 -0.0002 1.0000 0.6648
-1.500 -0.1785 0.00977 0.00270 0.0019 1.0000 0.8804
-1.250 -0.1339 0.00958 0.00243 -0.0013 1.0000 1.0000
-1.000 -0.1072 0.00954 0.00227 -0.0011 1.0000 1.0000
-0.750 -0.0804 0.00951 0.00216 -0.0008 1.0000 1.0000
-0.500 -0.0536 0.00949 0.00208 -0.0005 1.0000 1.0000
-0.250 -0.0268 0.00948 0.00202 -0.0003 1.0000 1.0000
0.000 0.0001 0.00948 0.00201 0.0000 1.0000 1.0000
0.250 0.0269 0.00948 0.00202 0.0003 1.0000 1.0000
0.500 0.0538 0.00949 0.00208 0.0005 1.0000 1.0000
0.750 0.0806 0.00951 0.00216 0.0008 1.0000 1.0000
1.000 0.1073 0.00954 0.00227 0.0011 1.0000 1.0000
1.250 0.1341 0.00958 0.00243 0.0013 1.0000 1.0000
1.500 0.1788 0.00977 0.00270 -0.0019 0.8785 1.0000
1.750 0.2044 0.01045 0.00277 0.0002 0.6639 1.0000
2.000 0.2269 0.01118 0.00292 0.0019 0.5269 1.0000
2.250 0.2522 0.01175 0.00314 0.0026 0.4406 1.0000
2.500 0.2783 0.01225 0.00342 0.0030 0.3693 1.0000
2.750 0.3047 0.01275 0.00369 0.0033 0.3010 1.0000
3.000 0.3312 0.01331 0.00399 0.0035 0.2304 1.0000
3.250 0.3576 0.01398 0.00437 0.0037 0.1644 1.0000
3.500 0.3842 0.01474 0.00491 0.0038 0.1153 1.0000
3.750 0.4109 0.01556 0.00566 0.0039 0.0872 1.0000
4.000 0.4375 0.01643 0.00647 0.0041 0.0695 1.0000
4.250 0.4642 0.01732 0.00744 0.0044 0.0586 1.0000
4.500 0.4907 0.01832 0.00852 0.0047 0.0502 1.0000
4.750 0.5168 0.01949 0.00978 0.0050 0.0453 1.0000
5.000 0.5430 0.02088 0.01132 0.0054 0.0405 1.0000
5.250 0.5694 0.02220 0.01286 0.0057 0.0363 1.0000
5.500 0.5953 0.02388 0.01472 0.0060 0.0340 1.0000
5.750 0.6200 0.02654 0.01760 0.0062 0.0322 1.0000
6.000 0.6460 0.02872 0.02045 0.0065 0.0297 1.0000
6.250 0.6704 0.03162 0.02392 0.0065 0.0276 1.0000
6.500 0.6927 0.03551 0.02844 0.0063 0.0267 1.0000
6.750 0.7124 0.04035 0.03392 0.0054 0.0261 1.0000
7.000 0.7282 0.04662 0.04082 0.0035 0.0260 1.0000
7.250 0.7389 0.05472 0.04947 -0.0003 0.0262 1.0000
7.500 0.7460 0.06383 0.05892 -0.0062 0.0266 1.0000
7.750 0.7515 0.07311 0.06837 -0.0141 0.0270 1.0000
8.000 0.7552 0.08111 0.07642 -0.0221 0.0272 1.0000
8.250 0.7558 0.08777 0.08306 -0.0287 0.0274 1.0000
8.500 0.7538 0.09334 0.08857 -0.0330 0.0274 1.0000
8.750 0.7524 0.09852 0.09371 -0.0364 0.0272 1.0000
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Polar data table (+)
Polar graphs
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