FX 66-H-60 (fx66h60-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-H-60 (fx66h60-il) Reynolds number: 100,000 Max Cl/Cd: 37.93 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66h60-il-100000.txt Download as CSV file: xf-fx66h60-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6258 0.11357 0.10903 0.0307 1.0000 0.0493
-8.500 -0.6287 0.11063 0.10616 0.0264 1.0000 0.0496
-8.250 -0.6325 0.10745 0.10304 0.0222 1.0000 0.0497
-8.000 -0.6335 0.10429 0.09986 0.0186 1.0000 0.0499
-7.750 -0.6320 0.10112 0.09662 0.0152 1.0000 0.0500
-7.500 -0.6173 0.09257 0.08826 0.0216 1.0000 0.0524
-7.250 -0.6110 0.08859 0.08422 0.0213 1.0000 0.0545
-7.000 -0.6058 0.08470 0.08033 0.0194 1.0000 0.0563
-6.750 -0.5996 0.08078 0.07639 0.0169 1.0000 0.0586
-6.500 -0.5907 0.07717 0.07267 0.0129 1.0000 0.0618
-6.250 -0.5791 0.07617 0.07119 0.0085 1.0000 0.0634
-6.000 -0.5704 0.06846 0.06377 0.0095 1.0000 0.0653
-5.750 -0.5585 0.06450 0.05983 0.0099 1.0000 0.0689
-5.500 -0.5381 0.06347 0.05822 0.0074 1.0000 0.0766
-5.250 -0.5268 0.05704 0.05198 0.0075 1.0000 0.0791
-5.000 -0.5108 0.05356 0.04847 0.0078 1.0000 0.0860
-4.750 -0.4941 0.04996 0.04473 0.0076 1.0000 0.0957
-4.500 -0.4766 0.04677 0.04140 0.0077 1.0000 0.1108
-4.250 -0.4573 0.04433 0.03860 0.0076 1.0000 0.1323
-4.000 -0.4399 0.04055 0.03489 0.0082 1.0000 0.1491
-3.750 -0.4219 0.03763 0.03190 0.0089 1.0000 0.1770
-3.250 -0.3714 0.01592 0.01081 0.0099 1.0000 0.2721
-3.000 -0.3540 0.01346 0.00839 0.0114 1.0000 0.3148
-2.750 -0.3291 0.01138 0.00611 0.0117 1.0000 0.3293
-2.500 -0.2668 0.02388 0.01566 0.0137 1.0000 0.0713
-2.250 -0.2365 0.02182 0.01315 0.0151 1.0000 0.0606
-2.000 -0.2082 0.01990 0.01102 0.0159 1.0000 0.0593
-1.750 -0.1799 0.01883 0.00970 0.0168 1.0000 0.0637
-1.500 -0.1524 0.01681 0.00775 0.0174 1.0000 0.0655
-1.250 -0.1266 0.01541 0.00644 0.0183 1.0000 0.0700
-1.000 -0.0138 0.01063 0.00445 0.0048 1.0000 1.0000
-0.750 0.0116 0.01054 0.00420 0.0050 1.0000 1.0000
-0.500 0.0649 0.01086 0.00405 -0.0003 0.8197 1.0000
-0.250 0.0886 0.01137 0.00394 0.0012 0.7286 1.0000
0.000 0.1116 0.01170 0.00387 0.0025 0.6749 1.0000
0.250 0.1348 0.01199 0.00383 0.0037 0.6349 1.0000
0.500 0.1572 0.01227 0.00383 0.0049 0.6030 1.0000
0.750 0.1804 0.01255 0.00387 0.0059 0.5757 1.0000
1.000 0.2041 0.01283 0.00394 0.0067 0.5523 1.0000
1.250 0.2279 0.01310 0.00406 0.0075 0.5308 1.0000
1.500 0.2515 0.01339 0.00419 0.0084 0.5127 1.0000
1.750 0.2751 0.01370 0.00436 0.0092 0.4966 1.0000
2.000 0.2989 0.01401 0.00460 0.0100 0.4807 1.0000
2.250 0.3227 0.01433 0.00486 0.0108 0.4667 1.0000
2.500 0.3466 0.01469 0.00519 0.0115 0.4542 1.0000
2.750 0.3704 0.01506 0.00550 0.0123 0.4425 1.0000
3.000 0.3945 0.01542 0.00588 0.0130 0.4308 1.0000
3.250 0.4186 0.01583 0.00634 0.0136 0.4201 1.0000
3.500 0.4427 0.01629 0.00684 0.0143 0.4106 1.0000
3.750 0.4667 0.01674 0.00734 0.0150 0.4022 1.0000
4.000 0.4909 0.01722 0.00798 0.0156 0.3924 1.0000
4.250 0.5151 0.01779 0.00867 0.0162 0.3846 1.0000
4.500 0.5392 0.01831 0.00927 0.0169 0.3768 1.0000
4.750 0.5633 0.01895 0.01014 0.0174 0.3685 1.0000
5.000 0.5876 0.01958 0.01084 0.0181 0.3623 1.0000
5.250 0.6116 0.02034 0.01202 0.0185 0.3539 1.0000
5.500 0.6359 0.02104 0.01288 0.0192 0.3473 1.0000
5.750 0.6592 0.02112 0.01316 0.0202 0.3314 1.0000
6.000 0.6801 0.01888 0.01072 0.0224 0.2865 1.0000
6.250 0.6979 0.01840 0.00940 0.0238 0.0789 1.0000
6.500 0.7168 0.02086 0.01186 0.0249 0.0536 1.0000
6.750 0.7349 0.02298 0.01412 0.0261 0.0473 1.0000
7.000 0.7550 0.02456 0.01585 0.0273 0.0422 1.0000
7.250 0.7724 0.02687 0.01816 0.0285 0.0374 1.0000
7.500 0.7927 0.02982 0.02113 0.0299 0.0363 1.0000
7.750 0.8145 0.03269 0.02423 0.0310 0.0362 1.0000
8.000 0.8350 0.03621 0.02805 0.0319 0.0366 1.0000
8.250 0.8559 0.03826 0.03054 0.0330 0.0376 1.0000
8.500 0.8715 0.04146 0.03454 0.0340 0.0402 1.0000
8.750 0.8783 0.04637 0.04016 0.0343 0.0433 1.0000
9.000 0.8819 0.05151 0.04570 0.0341 0.0458 1.0000
9.250 0.8291 0.04660 0.04145 0.0336 0.0467 1.0000
9.500 0.8695 0.06143 0.05649 0.0310 0.0515 1.0000
9.750 0.8485 0.06665 0.06190 0.0271 0.0517 1.0000
10.000 0.8301 0.07266 0.06797 0.0210 0.0513 1.0000
10.250 0.8110 0.08016 0.07549 0.0141 0.0510 1.0000
10.500 0.7900 0.08906 0.08437 0.0068 0.0510 1.0000
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Polar data table (+)
Polar graphs
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