HT05 (ht05-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT05 (ht05-il) Reynolds number: 100,000 Max Cl/Cd: 26.22 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht05-il-100000-n5.txt Download as CSV file: xf-ht05-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7347 0.09634 0.09142 0.0220 1.0000 0.0252
-8.750 -0.7373 0.09082 0.08594 0.0183 1.0000 0.0253
-8.500 -0.7408 0.08498 0.08015 0.0137 1.0000 0.0254
-8.250 -0.7406 0.07803 0.07318 0.0078 1.0000 0.0254
-8.000 -0.7385 0.07003 0.06510 0.0015 1.0000 0.0254
-7.750 -0.7366 0.06201 0.05685 -0.0033 1.0000 0.0254
-7.500 -0.7327 0.05487 0.04934 -0.0066 1.0000 0.0255
-7.250 -0.7257 0.04854 0.04259 -0.0084 1.0000 0.0257
-7.000 -0.7151 0.04282 0.03635 -0.0091 1.0000 0.0258
-6.750 -0.7010 0.03794 0.03094 -0.0093 1.0000 0.0262
-6.500 -0.6831 0.03420 0.02675 -0.0090 1.0000 0.0269
-6.250 -0.6626 0.03123 0.02330 -0.0086 1.0000 0.0279
-6.000 -0.6401 0.02899 0.02069 -0.0082 1.0000 0.0299
-5.750 -0.6164 0.02696 0.01822 -0.0076 1.0000 0.0331
-5.500 -0.5917 0.02471 0.01546 -0.0068 1.0000 0.0350
-5.250 -0.5673 0.02254 0.01301 -0.0061 1.0000 0.0369
-5.000 -0.5427 0.02117 0.01156 -0.0056 1.0000 0.0403
-4.750 -0.5172 0.02014 0.01027 -0.0050 1.0000 0.0461
-4.500 -0.4925 0.01878 0.00884 -0.0043 1.0000 0.0505
-4.250 -0.4672 0.01786 0.00782 -0.0037 1.0000 0.0579
-4.000 -0.4421 0.01698 0.00694 -0.0031 1.0000 0.0688
-3.750 -0.4168 0.01613 0.00608 -0.0025 1.0000 0.0820
-3.500 -0.3915 0.01541 0.00541 -0.0020 1.0000 0.1055
-3.250 -0.3660 0.01475 0.00486 -0.0015 1.0000 0.1371
-3.000 -0.3405 0.01416 0.00443 -0.0011 1.0000 0.1808
-2.750 -0.3151 0.01359 0.00406 -0.0006 1.0000 0.2329
-2.500 -0.2898 0.01302 0.00375 -0.0002 1.0000 0.2972
-2.250 -0.2647 0.01239 0.00348 0.0004 1.0000 0.3889
-2.000 -0.2408 0.01179 0.00339 0.0014 1.0000 0.5156
-1.750 -0.2160 0.01146 0.00319 0.0023 1.0000 0.6116
-1.500 -0.1924 0.01078 0.00289 0.0036 1.0000 0.6761
-1.250 -0.1224 0.01029 0.00292 -0.0040 1.0000 1.0000
-1.000 -0.0979 0.01025 0.00278 -0.0032 1.0000 1.0000
-0.750 -0.0734 0.01023 0.00267 -0.0024 1.0000 1.0000
-0.500 -0.0489 0.01021 0.00259 -0.0016 1.0000 1.0000
-0.250 -0.0244 0.01019 0.00255 -0.0008 1.0000 1.0000
0.000 0.0001 0.01019 0.00253 0.0000 1.0000 1.0000
0.250 0.0245 0.01019 0.00255 0.0008 1.0000 1.0000
0.500 0.0490 0.01020 0.00259 0.0016 1.0000 1.0000
0.750 0.0735 0.01023 0.00267 0.0024 1.0000 1.0000
1.000 0.0980 0.01025 0.00278 0.0032 1.0000 1.0000
1.250 0.1225 0.01029 0.00292 0.0040 1.0000 1.0000
1.500 0.1925 0.01079 0.00289 -0.0036 0.6754 1.0000
1.750 0.2161 0.01146 0.00319 -0.0023 0.6113 1.0000
2.000 0.2409 0.01179 0.00339 -0.0014 0.5149 1.0000
2.250 0.2648 0.01239 0.00348 -0.0004 0.3884 1.0000
2.500 0.2899 0.01302 0.00375 0.0002 0.2971 1.0000
2.750 0.3152 0.01360 0.00406 0.0006 0.2327 1.0000
3.000 0.3407 0.01416 0.00443 0.0011 0.1806 1.0000
3.250 0.3662 0.01475 0.00486 0.0015 0.1370 1.0000
3.500 0.3916 0.01541 0.00541 0.0020 0.1054 1.0000
3.750 0.4169 0.01613 0.00608 0.0025 0.0819 1.0000
4.000 0.4422 0.01699 0.00695 0.0031 0.0687 1.0000
4.250 0.4674 0.01785 0.00782 0.0037 0.0577 1.0000
4.500 0.4926 0.01879 0.00884 0.0043 0.0505 1.0000
4.750 0.5174 0.02014 0.01028 0.0050 0.0460 1.0000
5.000 0.5429 0.02116 0.01154 0.0056 0.0402 1.0000
5.250 0.5674 0.02257 0.01303 0.0061 0.0369 1.0000
5.500 0.5919 0.02472 0.01548 0.0068 0.0350 1.0000
5.750 0.6166 0.02698 0.01824 0.0076 0.0331 1.0000
6.000 0.6403 0.02896 0.02065 0.0081 0.0299 1.0000
6.250 0.6627 0.03122 0.02333 0.0086 0.0279 1.0000
6.500 0.6832 0.03419 0.02672 0.0090 0.0269 1.0000
6.750 0.7010 0.03799 0.03099 0.0092 0.0262 1.0000
7.000 0.7149 0.04298 0.03651 0.0091 0.0258 1.0000
7.500 0.7326 0.05510 0.04960 0.0065 0.0256 1.0000
7.750 0.7364 0.06241 0.05728 0.0030 0.0255 1.0000
8.000 0.7386 0.07057 0.06565 -0.0021 0.0254 1.0000
8.250 0.7407 0.07854 0.07370 -0.0085 0.0254 1.0000
8.500 0.7408 0.08538 0.08055 -0.0144 0.0254 1.0000
8.750 0.7373 0.09118 0.08630 -0.0189 0.0253 1.0000
9.000 0.7348 0.09666 0.09173 -0.0225 0.0252 1.0000
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Polar data table (+)
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