HT08 (ht08-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT08 (ht08-il) Reynolds number: 50,000 Max Cl/Cd: 20.07 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht08-il-50000-n5.txt Download as CSV file: xf-ht08-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7287 0.10270 0.09583 0.0291 1.0000 0.0495
-8.500 -0.7295 0.09769 0.09088 0.0258 1.0000 0.0492
-8.250 -0.7309 0.09242 0.08567 0.0218 1.0000 0.0488
-8.000 -0.7297 0.08650 0.07976 0.0165 1.0000 0.0485
-7.750 -0.7268 0.08024 0.07347 0.0112 1.0000 0.0483
-7.500 -0.7222 0.07396 0.06709 0.0066 1.0000 0.0482
-7.250 -0.7157 0.06772 0.06067 0.0025 1.0000 0.0483
-7.000 -0.7067 0.06156 0.05424 -0.0009 1.0000 0.0482
-6.750 -0.6949 0.05550 0.04778 -0.0036 1.0000 0.0480
-6.500 -0.6796 0.04992 0.04172 -0.0054 1.0000 0.0480
-6.250 -0.6613 0.04490 0.03610 -0.0066 1.0000 0.0485
-6.000 -0.6402 0.04051 0.03109 -0.0072 1.0000 0.0497
-5.750 -0.6168 0.03678 0.02662 -0.0074 1.0000 0.0535
-5.500 -0.5923 0.03351 0.02278 -0.0074 1.0000 0.0569
-5.250 -0.5672 0.03094 0.01990 -0.0071 1.0000 0.0598
-5.000 -0.5409 0.02864 0.01720 -0.0067 1.0000 0.0647
-4.750 -0.5149 0.02678 0.01511 -0.0063 1.0000 0.0727
-4.500 -0.4881 0.02497 0.01293 -0.0056 1.0000 0.0802
-4.250 -0.4621 0.02352 0.01139 -0.0051 1.0000 0.0928
-4.000 -0.4355 0.02212 0.00990 -0.0046 1.0000 0.1089
-3.750 -0.4089 0.02087 0.00868 -0.0043 1.0000 0.1361
-3.500 -0.3829 0.01959 0.00753 -0.0041 1.0000 0.1785
-3.250 -0.3576 0.01831 0.00667 -0.0039 1.0000 0.2550
-3.000 -0.3339 0.01704 0.00602 -0.0033 1.0000 0.3778
-2.750 -0.3141 0.01575 0.00558 -0.0013 1.0000 0.5481
-2.500 -0.2946 0.01467 0.00538 0.0027 1.0000 0.7782
-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 0.2947 0.01468 0.00538 -0.0027 0.7768 1.0000
2.750 0.3142 0.01576 0.00558 0.0013 0.5471 1.0000
3.000 0.3340 0.01705 0.00602 0.0033 0.3772 1.0000
3.250 0.3577 0.01831 0.00667 0.0039 0.2546 1.0000
3.500 0.3830 0.01959 0.00753 0.0041 0.1782 1.0000
3.750 0.4091 0.02088 0.00867 0.0043 0.1359 1.0000
4.000 0.4357 0.02213 0.00991 0.0046 0.1089 1.0000
4.250 0.4622 0.02352 0.01140 0.0051 0.0927 1.0000
4.500 0.4882 0.02498 0.01294 0.0056 0.0802 1.0000
4.750 0.5151 0.02679 0.01512 0.0063 0.0727 1.0000
5.000 0.5410 0.02866 0.01721 0.0067 0.0647 1.0000
5.250 0.5674 0.03095 0.01992 0.0071 0.0598 1.0000
5.500 0.5925 0.03352 0.02280 0.0074 0.0568 1.0000
5.750 0.6170 0.03680 0.02665 0.0074 0.0535 1.0000
6.000 0.6404 0.04053 0.03112 0.0071 0.0497 1.0000
6.250 0.6615 0.04493 0.03613 0.0065 0.0485 1.0000
6.500 0.6798 0.04995 0.04176 0.0054 0.0480 1.0000
6.750 0.6951 0.05554 0.04782 0.0035 0.0480 1.0000
7.000 0.7069 0.06160 0.05428 0.0008 0.0482 1.0000
7.250 0.7159 0.06777 0.06072 -0.0026 0.0483 1.0000
7.500 0.7225 0.07401 0.06714 -0.0066 0.0482 1.0000
7.750 0.7271 0.08030 0.07352 -0.0113 0.0483 1.0000
8.000 0.7301 0.08655 0.07981 -0.0166 0.0485 1.0000
8.250 0.7313 0.09248 0.08573 -0.0219 0.0488 1.0000
8.500 0.7299 0.09775 0.09093 -0.0260 0.0491 1.0000
8.750 0.7292 0.10276 0.09590 -0.0292 0.0495 1.0000
9.000 0.7291 0.10763 0.10072 -0.0320 0.0501 1.0000
9.250 0.7297 0.11240 0.10544 -0.0343 0.0511 1.0000
9.500 0.7318 0.11701 0.11002 -0.0361 0.0525 1.0000
9.750 0.7374 0.12138 0.11439 -0.0364 0.0543 1.0000
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Polar data table (+)
Polar graphs
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