HT08 (ht08-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT08 (ht08-il) Reynolds number: 50,000 Max Cl/Cd: 21.57 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht08-il-50000.txt Download as CSV file: xf-ht08-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HT08
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.7011 0.09435 0.08786 0.0451 1.0000 0.2990
-7.000 -0.7008 0.09087 0.08443 0.0444 1.0000 0.3154
-6.750 -0.7009 0.08718 0.08081 0.0429 1.0000 0.3337
-6.500 -0.6952 0.08384 0.07745 0.0436 1.0000 0.3600
-6.250 -0.6864 0.08015 0.07380 0.0461 1.0000 0.3898
-5.750 -0.6299 0.04955 0.04123 -0.0059 1.0000 0.1367
-5.500 -0.6065 0.04480 0.03604 -0.0069 1.0000 0.1346
-5.250 -0.5818 0.04018 0.03098 -0.0075 1.0000 0.1319
-5.000 -0.5550 0.03584 0.02599 -0.0080 1.0000 0.1299
-4.750 -0.5269 0.03241 0.02176 -0.0081 1.0000 0.1343
-4.500 -0.5003 0.02973 0.01885 -0.0078 1.0000 0.1448
-4.250 -0.4714 0.02695 0.01562 -0.0074 1.0000 0.1535
-4.000 -0.4440 0.02500 0.01349 -0.0069 1.0000 0.1755
-3.750 -0.4162 0.02287 0.01135 -0.0062 1.0000 0.2012
-3.500 -0.3893 0.02102 0.00964 -0.0054 1.0000 0.2518
-3.250 -0.3638 0.01893 0.00811 -0.0043 1.0000 0.3501
-3.000 -0.3483 0.01614 0.00700 -0.0005 1.0000 0.5828
-2.750 -0.2770 0.01463 0.00599 -0.0040 1.0000 1.0000
-2.500 -0.2529 0.01439 0.00525 -0.0038 1.0000 1.0000
-2.250 -0.2284 0.01422 0.00471 -0.0035 1.0000 1.0000
-2.000 -0.2037 0.01409 0.00427 -0.0031 1.0000 1.0000
-1.750 -0.1787 0.01397 0.00390 -0.0027 1.0000 1.0000
-1.500 -0.1535 0.01389 0.00358 -0.0023 1.0000 1.0000
-1.250 -0.1281 0.01381 0.00333 -0.0019 1.0000 1.0000
-1.000 -0.1026 0.01376 0.00313 -0.0015 1.0000 1.0000
-0.750 -0.0770 0.01371 0.00298 -0.0011 1.0000 1.0000
-0.500 -0.0514 0.01368 0.00288 -0.0008 1.0000 1.0000
-0.250 -0.0257 0.01366 0.00281 -0.0004 1.0000 1.0000
0.000 0.0001 0.01366 0.00278 0.0000 1.0000 1.0000
0.250 0.0258 0.01366 0.00281 0.0004 1.0000 1.0000
0.500 0.0515 0.01368 0.00288 0.0008 1.0000 1.0000
0.750 0.0772 0.01371 0.00298 0.0011 1.0000 1.0000
1.000 0.1028 0.01376 0.00313 0.0015 1.0000 1.0000
1.250 0.1282 0.01381 0.00333 0.0019 1.0000 1.0000
1.500 0.1536 0.01389 0.00358 0.0023 1.0000 1.0000
1.750 0.1788 0.01398 0.00391 0.0027 1.0000 1.0000
2.000 0.2038 0.01409 0.00427 0.0031 1.0000 1.0000
2.250 0.2286 0.01422 0.00471 0.0035 1.0000 1.0000
2.500 0.2531 0.01439 0.00525 0.0038 1.0000 1.0000
2.750 0.2772 0.01463 0.00599 0.0040 1.0000 1.0000
3.000 0.3483 0.01615 0.00701 0.0006 0.5812 1.0000
3.250 0.3639 0.01894 0.00812 0.0043 0.3496 1.0000
3.500 0.3895 0.02103 0.00965 0.0054 0.2515 1.0000
3.750 0.4163 0.02288 0.01136 0.0062 0.2009 1.0000
4.000 0.4442 0.02501 0.01350 0.0069 0.1754 1.0000
4.250 0.4715 0.02696 0.01563 0.0074 0.1534 1.0000
4.500 0.5004 0.02975 0.01887 0.0078 0.1448 1.0000
4.750 0.5271 0.03243 0.02178 0.0081 0.1343 1.0000
5.000 0.5551 0.03586 0.02601 0.0080 0.1299 1.0000
5.250 0.5820 0.04021 0.03101 0.0075 0.1320 1.0000
5.500 0.6067 0.04483 0.03607 0.0068 0.1346 1.0000
5.750 0.6301 0.04959 0.04127 0.0059 0.1367 1.0000
6.250 0.6875 0.08025 0.07390 -0.0459 0.3896 1.0000
6.500 0.6945 0.08381 0.07742 -0.0440 0.3598 1.0000
6.750 0.7019 0.08725 0.08089 -0.0428 0.3336 1.0000
7.000 0.7005 0.09084 0.08441 -0.0446 0.3150 1.0000
7.250 0.7014 0.09437 0.08788 -0.0452 0.2988 1.0000
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Polar data table (+)
Polar graphs
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