FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 500,000 Max Cl/Cd: 73.24 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx68h120-il-500000-n5.txt Download as CSV file: xf-fx68h120-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 68-H-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6975 0.09545 0.09303 -0.0161 1.0000 0.0050
-13.500 -0.7147 0.08768 0.08517 -0.0207 1.0000 0.0048
-13.250 -0.7395 0.07896 0.07636 -0.0260 1.0000 0.0048
-13.000 -0.7676 0.06972 0.06703 -0.0319 1.0000 0.0048
-12.750 -0.7957 0.06006 0.05725 -0.0386 1.0000 0.0048
-12.500 -0.7986 0.05440 0.05151 -0.0431 0.9836 0.0047
-12.250 -0.8078 0.04509 0.04190 -0.0543 0.9472 0.0047
-12.000 -0.8315 0.03992 0.03648 -0.0569 0.9265 0.0047
-11.750 -0.8444 0.03729 0.03364 -0.0556 0.9147 0.0047
-11.500 -0.8636 0.03453 0.03065 -0.0523 0.9047 0.0047
-11.250 -0.8765 0.03223 0.02812 -0.0484 0.8971 0.0048
-11.000 -0.8799 0.02998 0.02562 -0.0455 0.8914 0.0049
-10.750 -0.8745 0.02817 0.02361 -0.0434 0.8868 0.0051
-10.500 -0.8631 0.02672 0.02200 -0.0418 0.8824 0.0052
-10.250 -0.8491 0.02550 0.02063 -0.0403 0.8788 0.0053
-10.000 -0.8337 0.02435 0.01933 -0.0389 0.8758 0.0054
-9.750 -0.8151 0.02338 0.01823 -0.0379 0.8725 0.0056
-9.500 -0.7970 0.02227 0.01696 -0.0367 0.8691 0.0058
-9.250 -0.7774 0.02136 0.01591 -0.0357 0.8659 0.0060
-9.000 -0.7575 0.02046 0.01487 -0.0346 0.8631 0.0062
-8.750 -0.7369 0.01958 0.01384 -0.0336 0.8606 0.0064
-8.500 -0.7145 0.01880 0.01295 -0.0329 0.8577 0.0067
-8.250 -0.6920 0.01806 0.01210 -0.0321 0.8548 0.0069
-8.000 -0.6686 0.01745 0.01137 -0.0314 0.8521 0.0072
-7.750 -0.6454 0.01682 0.01064 -0.0307 0.8495 0.0075
-7.500 -0.6241 0.01589 0.00958 -0.0296 0.8472 0.0080
-7.250 -0.5998 0.01525 0.00885 -0.0291 0.8446 0.0086
-7.000 -0.5748 0.01471 0.00824 -0.0286 0.8420 0.0090
-6.750 -0.5495 0.01423 0.00768 -0.0281 0.8393 0.0095
-6.500 -0.5240 0.01379 0.00716 -0.0276 0.8368 0.0101
-6.250 -0.4984 0.01340 0.00667 -0.0271 0.8346 0.0107
-6.000 -0.4723 0.01302 0.00622 -0.0267 0.8326 0.0114
-5.750 -0.4462 0.01256 0.00573 -0.0264 0.8300 0.0135
-5.500 -0.4196 0.01222 0.00533 -0.0261 0.8272 0.0164
-5.250 -0.3937 0.01179 0.00492 -0.0257 0.8246 0.0248
-5.000 -0.3685 0.01131 0.00451 -0.0252 0.8218 0.0436
-4.750 -0.3435 0.01085 0.00416 -0.0246 0.8167 0.0694
-4.500 -0.3175 0.01052 0.00391 -0.0242 0.8091 0.0923
-4.250 -0.2909 0.01031 0.00370 -0.0238 0.8026 0.1059
-4.000 -0.2636 0.01013 0.00354 -0.0236 0.7965 0.1212
-3.750 -0.2366 0.00999 0.00340 -0.0233 0.7913 0.1356
-3.500 -0.2091 0.00981 0.00325 -0.0231 0.7846 0.1445
-3.250 -0.1817 0.00969 0.00308 -0.0229 0.7786 0.1503
-3.000 -0.1542 0.00953 0.00292 -0.0227 0.7726 0.1559
-2.750 -0.1267 0.00941 0.00276 -0.0225 0.7659 0.1612
-2.500 -0.0992 0.00928 0.00261 -0.0223 0.7591 0.1671
-2.250 -0.0717 0.00916 0.00248 -0.0221 0.7515 0.1734
-2.000 -0.0441 0.00905 0.00234 -0.0219 0.7427 0.1798
-1.750 -0.0168 0.00893 0.00221 -0.0217 0.7309 0.1890
-1.500 0.0102 0.00881 0.00209 -0.0214 0.7143 0.2005
-1.250 0.0371 0.00872 0.00196 -0.0211 0.6941 0.2138
-1.000 0.0636 0.00866 0.00184 -0.0207 0.6647 0.2312
-0.750 0.0890 0.00868 0.00175 -0.0201 0.6149 0.2539
-0.500 0.1129 0.00884 0.00172 -0.0195 0.5484 0.2860
0.000 0.1607 0.00895 0.00179 -0.0183 0.4630 0.3892
0.250 0.1846 0.00890 0.00182 -0.0176 0.4342 0.4523
0.500 0.2078 0.00879 0.00186 -0.0168 0.4114 0.5249
0.750 0.2299 0.00864 0.00189 -0.0157 0.3913 0.6071
1.000 0.2493 0.00840 0.00194 -0.0140 0.3722 0.7117
1.250 0.2713 0.00813 0.00205 -0.0125 0.3530 0.8414
1.500 0.3296 0.00833 0.00230 -0.0189 0.3282 0.9198
1.750 0.3708 0.00856 0.00243 -0.0219 0.3109 0.9395
2.000 0.4075 0.00878 0.00255 -0.0238 0.2959 0.9518
2.250 0.4406 0.00899 0.00268 -0.0249 0.2822 0.9611
2.500 0.4733 0.00922 0.00283 -0.0259 0.2689 0.9716
2.750 0.5234 0.00954 0.00305 -0.0307 0.2527 0.9848
3.000 0.5756 0.00981 0.00321 -0.0360 0.2371 0.9931
3.250 0.6180 0.00998 0.00331 -0.0393 0.2254 0.9973
3.500 0.6564 0.01014 0.00343 -0.0417 0.2159 1.0000
3.750 0.6800 0.01032 0.00355 -0.0410 0.2085 1.0000
4.000 0.7038 0.01047 0.00368 -0.0403 0.2020 1.0000
4.500 0.7506 0.01083 0.00400 -0.0388 0.1905 1.0000
4.750 0.7738 0.01103 0.00417 -0.0380 0.1854 1.0000
5.000 0.7967 0.01124 0.00436 -0.0372 0.1807 1.0000
5.250 0.8199 0.01143 0.00455 -0.0364 0.1759 1.0000
5.500 0.8419 0.01170 0.00476 -0.0355 0.1676 1.0000
5.750 0.8646 0.01191 0.00497 -0.0346 0.1608 1.0000
6.000 0.8864 0.01219 0.00521 -0.0336 0.1541 1.0000
6.250 0.9086 0.01242 0.00542 -0.0327 0.1455 1.0000
6.500 0.9301 0.01270 0.00567 -0.0316 0.1382 1.0000
6.750 0.9509 0.01303 0.00594 -0.0305 0.1266 1.0000
7.000 0.9665 0.01381 0.00642 -0.0287 0.0848 1.0000
7.250 0.9722 0.01543 0.00768 -0.0255 0.0111 1.0000
7.500 0.9913 0.01585 0.00815 -0.0240 0.0086 1.0000
7.750 1.0105 0.01624 0.00859 -0.0226 0.0078 1.0000
8.000 1.0291 0.01666 0.00907 -0.0211 0.0071 1.0000
8.250 1.0465 0.01716 0.00963 -0.0195 0.0063 1.0000
8.500 1.0623 0.01777 0.01033 -0.0176 0.0055 1.0000
8.750 1.0790 0.01828 0.01093 -0.0159 0.0052 1.0000
9.000 1.0944 0.01886 0.01159 -0.0140 0.0050 1.0000
9.250 1.1087 0.01949 0.01230 -0.0120 0.0047 1.0000
9.500 1.1202 0.02015 0.01303 -0.0096 0.0043 1.0000
9.750 1.1285 0.02086 0.01382 -0.0067 0.0042 1.0000
10.000 1.1366 0.02166 0.01470 -0.0040 0.0041 1.0000
10.250 1.1452 0.02253 0.01565 -0.0015 0.0040 1.0000
10.500 1.1531 0.02350 0.01670 0.0007 0.0038 1.0000
10.750 1.1595 0.02463 0.01792 0.0030 0.0037 1.0000
11.000 1.1638 0.02598 0.01935 0.0052 0.0036 1.0000
11.250 1.1652 0.02758 0.02108 0.0074 0.0035 1.0000
11.500 1.1668 0.02926 0.02287 0.0093 0.0034 1.0000
11.750 1.1675 0.03112 0.02484 0.0109 0.0034 1.0000
12.000 1.1530 0.03440 0.02826 0.0129 0.0033 1.0000
12.250 1.1513 0.03680 0.03077 0.0138 0.0033 1.0000
12.500 1.1479 0.03957 0.03365 0.0143 0.0033 1.0000
12.750 1.1455 0.04245 0.03665 0.0145 0.0032 1.0000
13.000 1.1375 0.04623 0.04056 0.0140 0.0032 1.0000
13.250 1.1311 0.05014 0.04458 0.0131 0.0032 1.0000
13.500 1.1216 0.05480 0.04937 0.0115 0.0032 1.0000
13.750 1.1147 0.05945 0.05414 0.0098 0.0032 1.0000
14.000 1.1072 0.06425 0.05906 0.0078 0.0032 1.0000
14.250 1.0980 0.06932 0.06423 0.0059 0.0032 1.0000
14.500 1.0894 0.07429 0.06930 0.0040 0.0031 1.0000
14.750 1.0819 0.07910 0.07419 0.0022 0.0031 1.0000
15.000 1.0745 0.08375 0.07892 0.0006 0.0032 1.0000
15.250 1.0686 0.08836 0.08362 -0.0010 0.0031 1.0000
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