FX 66-H-60 (fx66h60-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-H-60 (fx66h60-il) Reynolds number: 50,000 Max Cl/Cd: 29.85 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66h60-il-50000-n5.txt Download as CSV file: xf-fx66h60-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-H-60
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 -0.6241 0.11515 0.10874 0.0343 1.0000 0.0800
-8.500 -0.6277 0.11226 0.10593 0.0306 1.0000 0.0823
-8.250 -0.6341 0.10936 0.10313 0.0261 1.0000 0.0831
-8.000 -0.6190 0.10375 0.09755 0.0289 1.0000 0.0888
-7.750 -0.6191 0.10024 0.09411 0.0267 1.0000 0.0929
-7.500 -0.6262 0.09738 0.09130 0.0214 1.0000 0.0960
-7.000 -0.6128 0.08872 0.08271 0.0204 1.0000 0.1059
-6.500 -0.6013 0.08071 0.07472 0.0168 1.0000 0.1170
-6.250 -0.5967 0.07708 0.07099 0.0134 1.0000 0.1255
-6.000 -0.5844 0.07291 0.06684 0.0138 1.0000 0.1328
-5.750 -0.5742 0.06894 0.06282 0.0129 1.0000 0.1434
-5.500 -0.5218 0.05348 0.04791 0.0111 1.0000 0.1680
-5.000 -0.5041 0.05518 0.04799 0.0074 1.0000 0.0681
-4.750 -0.4820 0.05059 0.04314 0.0075 1.0000 0.0527
-4.250 -0.4343 0.04349 0.03511 0.0085 1.0000 0.0424
-4.000 -0.4123 0.04010 0.03146 0.0090 1.0000 0.0411
-3.750 -0.3885 0.03708 0.02807 0.0096 1.0000 0.0398
-3.500 -0.3633 0.03428 0.02475 0.0104 1.0000 0.0388
-3.250 -0.3370 0.03172 0.02179 0.0111 1.0000 0.0381
-3.000 -0.3098 0.02938 0.01907 0.0119 1.0000 0.0377
-2.750 -0.2818 0.02730 0.01663 0.0126 1.0000 0.0385
-2.500 -0.2531 0.02571 0.01463 0.0134 1.0000 0.0425
-2.250 -0.2248 0.02383 0.01265 0.0137 1.0000 0.0470
-2.000 -0.1938 0.02225 0.01092 0.0141 1.0000 0.0500
-1.750 -0.1633 0.02089 0.00935 0.0145 1.0000 0.0541
-1.500 -0.1376 0.01968 0.00804 0.0153 1.0000 0.0606
-1.250 -0.0388 0.01461 0.00598 0.0040 1.0000 1.0000
-1.000 -0.0142 0.01451 0.00548 0.0046 1.0000 1.0000
-0.750 0.0104 0.01443 0.00518 0.0049 1.0000 1.0000
-0.500 0.0525 0.01467 0.00496 0.0020 0.8261 1.0000
-0.250 0.0796 0.01511 0.00478 0.0028 0.7385 1.0000
0.000 0.1018 0.01547 0.00469 0.0043 0.6846 1.0000
0.250 0.1240 0.01579 0.00463 0.0057 0.6434 1.0000
0.500 0.1468 0.01609 0.00461 0.0069 0.6098 1.0000
0.750 0.1700 0.01637 0.00463 0.0079 0.5815 1.0000
1.000 0.1936 0.01666 0.00469 0.0088 0.5564 1.0000
1.250 0.2176 0.01694 0.00479 0.0096 0.5341 1.0000
1.500 0.2416 0.01725 0.00492 0.0103 0.5148 1.0000
1.750 0.2659 0.01755 0.00511 0.0110 0.4966 1.0000
2.000 0.2903 0.01787 0.00534 0.0116 0.4799 1.0000
2.250 0.3148 0.01820 0.00562 0.0122 0.4650 1.0000
2.500 0.3394 0.01855 0.00601 0.0128 0.4511 1.0000
2.750 0.3640 0.01892 0.00637 0.0134 0.4381 1.0000
3.000 0.3886 0.01931 0.00679 0.0140 0.4261 1.0000
3.250 0.4127 0.01973 0.00725 0.0146 0.4151 1.0000
3.500 0.4367 0.02018 0.00772 0.0153 0.4050 1.0000
3.750 0.4613 0.02066 0.00831 0.0158 0.3948 1.0000
4.000 0.4862 0.02119 0.00912 0.0163 0.3848 1.0000
4.250 0.5107 0.02174 0.00981 0.0168 0.3761 1.0000
4.500 0.5350 0.02232 0.01054 0.0174 0.3677 1.0000
4.750 0.5594 0.02299 0.01146 0.0178 0.3588 1.0000
5.000 0.5836 0.02364 0.01227 0.0184 0.3516 1.0000
5.250 0.6079 0.02442 0.01339 0.0188 0.3432 1.0000
5.500 0.6321 0.02522 0.01449 0.0193 0.3355 1.0000
5.750 0.6562 0.02604 0.01583 0.0199 0.3280 1.0000
6.000 0.6802 0.02704 0.01731 0.0203 0.3197 1.0000
6.250 0.7028 0.02664 0.01711 0.0219 0.2982 1.0000
6.500 0.7215 0.02417 0.01467 0.0237 0.2030 1.0000
6.750 0.7360 0.02701 0.01648 0.0237 0.0662 1.0000
7.000 0.7515 0.02994 0.01945 0.0239 0.0482 1.0000
7.250 0.7654 0.03267 0.02233 0.0240 0.0400 1.0000
7.500 0.7807 0.03487 0.02486 0.0248 0.0368 1.0000
7.750 0.7947 0.03719 0.02742 0.0258 0.0342 1.0000
8.000 0.8083 0.03957 0.03000 0.0269 0.0325 1.0000
8.250 0.8217 0.04224 0.03285 0.0281 0.0311 1.0000
8.500 0.8332 0.04571 0.03658 0.0292 0.0295 1.0000
8.750 0.8439 0.04864 0.04001 0.0294 0.0282 1.0000
9.000 0.8496 0.05208 0.04389 0.0292 0.0269 1.0000
9.250 0.8501 0.05590 0.04808 0.0283 0.0259 1.0000
9.500 0.8459 0.06002 0.05248 0.0268 0.0257 1.0000
9.750 0.8352 0.06452 0.05715 0.0241 0.0256 1.0000
10.000 0.8246 0.06992 0.06270 0.0200 0.0260 1.0000
10.250 0.8142 0.07576 0.06867 0.0157 0.0264 1.0000
10.500 0.8026 0.08224 0.07524 0.0112 0.0268 1.0000
10.750 0.7915 0.08887 0.08193 0.0068 0.0272 1.0000
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Polar data table (+)
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