US1000ROOT (us1000root-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: US1000ROOT (us1000root-il) Reynolds number: 100,000 Max Cl/Cd: 38.65 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-us1000root-il-100000-n5.txt Download as CSV file: xf-us1000root-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: US1000ROOT
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.7039 0.11227 0.10508 -0.0154 1.0000 0.0194
-15.000 -0.7101 0.10749 0.10022 -0.0172 1.0000 0.0203
-14.750 -0.7211 0.10198 0.09461 -0.0192 1.0000 0.0223
-14.500 -0.7269 0.09740 0.08993 -0.0209 1.0000 0.0226
-14.250 -0.7360 0.09237 0.08477 -0.0226 1.0000 0.0245
-14.000 -0.7428 0.08780 0.08012 -0.0242 1.0000 0.0250
-13.750 -0.7523 0.08291 0.07512 -0.0259 1.0000 0.0253
-13.500 -0.7687 0.07717 0.06928 -0.0279 1.0000 0.0269
-13.250 -0.7886 0.07110 0.06310 -0.0299 1.0000 0.0293
-13.000 -0.8092 0.06515 0.05705 -0.0318 1.0000 0.0331
-12.750 -0.8055 0.06251 0.05425 -0.0325 1.0000 0.0298
-12.500 -0.8353 0.05575 0.04741 -0.0345 1.0000 0.0362
-12.250 -0.8483 0.05133 0.04290 -0.0355 1.0000 0.0383
-11.500 -0.9281 0.03647 0.02834 -0.0356 1.0000 0.1045
-11.250 -0.9461 0.03340 0.02544 -0.0337 1.0000 0.1307
-11.000 -0.9576 0.03121 0.02338 -0.0312 1.0000 0.1548
-10.750 -0.9675 0.02952 0.02183 -0.0281 1.0000 0.1813
-10.500 -0.9801 0.02829 0.02068 -0.0238 1.0000 0.2102
-10.250 -0.9887 0.02764 0.02008 -0.0190 1.0000 0.2266
-10.000 -0.9953 0.02717 0.01953 -0.0138 1.0000 0.2388
-9.750 -0.9954 0.02684 0.01922 -0.0095 1.0000 0.2485
-9.500 -0.9909 0.02643 0.01873 -0.0059 1.0000 0.2566
-9.250 -0.9843 0.02605 0.01824 -0.0025 1.0000 0.2637
-9.000 -0.9772 0.02569 0.01780 0.0007 1.0000 0.2702
-8.750 -0.9708 0.02543 0.01751 0.0041 1.0000 0.2771
-8.500 -0.9671 0.02510 0.01707 0.0080 1.0000 0.2833
-8.250 -0.9616 0.02493 0.01692 0.0115 1.0000 0.2888
-8.000 -0.9465 0.02457 0.01640 0.0131 0.9969 0.2954
-7.750 -0.9111 0.02414 0.01592 0.0110 0.9875 0.3012
-7.500 -0.8787 0.02368 0.01532 0.0095 0.9760 0.3077
-7.250 -0.8458 0.02321 0.01474 0.0080 0.9646 0.3136
-7.000 -0.8102 0.02279 0.01422 0.0061 0.9547 0.3197
-6.750 -0.7747 0.02230 0.01357 0.0042 0.9453 0.3265
-6.500 -0.7379 0.02189 0.01315 0.0022 0.9363 0.3321
-6.250 -0.6970 0.02142 0.01252 -0.0007 0.9291 0.3392
-6.000 -0.6585 0.02102 0.01208 -0.0030 0.9197 0.3449
-5.750 -0.6159 0.02060 0.01157 -0.0062 0.9118 0.3520
-5.500 -0.5762 0.02022 0.01112 -0.0087 0.9020 0.3582
-5.250 -0.5388 0.01989 0.01073 -0.0108 0.8912 0.3651
-5.000 -0.5018 0.01957 0.01032 -0.0128 0.8800 0.3721
-4.750 -0.4656 0.01929 0.01000 -0.0145 0.8684 0.3788
-4.500 -0.4325 0.01903 0.00966 -0.0156 0.8558 0.3860
-4.250 -0.4036 0.01882 0.00943 -0.0159 0.8419 0.3930
-4.000 -0.3769 0.01863 0.00917 -0.0157 0.8277 0.4009
-3.750 -0.3508 0.01844 0.00898 -0.0153 0.8130 0.4081
-3.500 -0.3257 0.01825 0.00874 -0.0147 0.7981 0.4160
-3.250 -0.3010 0.01806 0.00853 -0.0139 0.7828 0.4238
-3.000 -0.2773 0.01788 0.00833 -0.0130 0.7668 0.4321
-2.750 -0.2544 0.01772 0.00814 -0.0119 0.7501 0.4413
-2.500 -0.2309 0.01755 0.00797 -0.0109 0.7334 0.4501
-2.250 -0.2075 0.01739 0.00777 -0.0099 0.7163 0.4598
-2.000 -0.1838 0.01725 0.00761 -0.0089 0.6993 0.4695
-1.750 -0.1600 0.01711 0.00745 -0.0079 0.6822 0.4796
-1.500 -0.1365 0.01700 0.00730 -0.0069 0.6654 0.4908
-1.250 -0.1140 0.01691 0.00716 -0.0057 0.6480 0.5027
-1.000 -0.0912 0.01684 0.00709 -0.0046 0.6309 0.5143
-0.750 -0.0685 0.01678 0.00702 -0.0034 0.6139 0.5265
-0.500 -0.0459 0.01674 0.00697 -0.0022 0.5980 0.5395
-0.250 -0.0233 0.01671 0.00694 -0.0010 0.5825 0.5533
0.000 -0.0008 0.01670 0.00693 0.0002 0.5675 0.5674
0.250 0.0217 0.01671 0.00694 0.0014 0.5532 0.5824
0.500 0.0442 0.01674 0.00697 0.0026 0.5395 0.5980
0.750 0.0669 0.01678 0.00702 0.0037 0.5267 0.6139
1.000 0.0896 0.01683 0.00709 0.0049 0.5145 0.6307
1.250 0.1124 0.01691 0.00717 0.0061 0.5029 0.6479
1.500 0.1350 0.01700 0.00730 0.0072 0.4911 0.6652
1.750 0.1585 0.01711 0.00746 0.0083 0.4798 0.6823
2.000 0.1823 0.01724 0.00761 0.0092 0.4698 0.6992
2.250 0.2059 0.01739 0.00778 0.0102 0.4599 0.7163
2.500 0.2294 0.01754 0.00798 0.0113 0.4501 0.7333
2.750 0.2528 0.01771 0.00815 0.0123 0.4414 0.7503
3.000 0.2758 0.01788 0.00834 0.0133 0.4321 0.7668
3.250 0.2994 0.01805 0.00854 0.0143 0.4238 0.7828
3.500 0.3242 0.01824 0.00875 0.0150 0.4160 0.7981
3.750 0.3493 0.01843 0.00898 0.0156 0.4082 0.8129
4.000 0.3755 0.01862 0.00919 0.0160 0.4008 0.8277
4.250 0.4024 0.01882 0.00946 0.0162 0.3929 0.8420
4.500 0.4313 0.01902 0.00968 0.0159 0.3860 0.8559
4.750 0.4646 0.01928 0.01002 0.0148 0.3789 0.8685
5.000 0.5009 0.01956 0.01034 0.0130 0.3720 0.8801
5.250 0.5382 0.01988 0.01076 0.0110 0.3649 0.8914
5.500 0.5760 0.02021 0.01115 0.0088 0.3581 0.9022
5.750 0.6156 0.02060 0.01161 0.0063 0.3519 0.9120
6.000 0.6584 0.02101 0.01213 0.0031 0.3449 0.9197
6.250 0.6969 0.02141 0.01257 0.0008 0.3391 0.9291
6.500 0.7364 0.02178 0.01307 -0.0018 0.3295 0.9366
6.750 0.7702 0.02208 0.01345 -0.0034 0.3180 0.9464
7.000 0.8008 0.02232 0.01372 -0.0044 0.3032 0.9579
7.250 0.8326 0.02264 0.01413 -0.0057 0.2910 0.9699
7.500 0.8646 0.02304 0.01459 -0.0071 0.2832 0.9825
7.750 0.8969 0.02343 0.01507 -0.0088 0.2697 0.9948
8.000 0.9183 0.02376 0.01552 -0.0085 0.2604 1.0000
8.250 0.9205 0.02400 0.01578 -0.0044 0.2554 1.0000
8.500 0.9192 0.02426 0.01605 0.0002 0.2420 1.0000
8.750 0.9147 0.02468 0.01637 0.0052 0.2182 1.0000
9.000 0.9052 0.02538 0.01684 0.0107 0.1830 1.0000
9.250 0.8963 0.02624 0.01749 0.0160 0.1549 1.0000
9.500 0.8843 0.02751 0.01853 0.0211 0.1257 1.0000
9.750 0.8611 0.02976 0.02042 0.0264 0.0773 1.0000
10.000 0.8320 0.03293 0.02327 0.0307 0.0335 1.0000
10.250 0.8177 0.03562 0.02595 0.0331 0.0240 1.0000
10.500 0.8157 0.03768 0.02813 0.0344 0.0221 1.0000
10.750 0.8123 0.04004 0.03060 0.0352 0.0206 1.0000
11.000 0.8020 0.04331 0.03402 0.0357 0.0183 1.0000
11.250 0.7938 0.04667 0.03749 0.0356 0.0168 1.0000
11.500 0.7820 0.05071 0.04167 0.0350 0.0140 1.0000
11.750 0.7747 0.05446 0.04556 0.0341 0.0139 1.0000
12.000 0.7671 0.05843 0.04968 0.0331 0.0144 1.0000
12.250 0.7583 0.06267 0.05405 0.0319 0.0140 1.0000
12.500 0.7475 0.06729 0.05881 0.0305 0.0137 1.0000
12.750 0.7310 0.07281 0.06442 0.0286 0.0123 1.0000
13.000 0.7265 0.07680 0.06853 0.0274 0.0125 1.0000
13.250 0.7173 0.08156 0.07343 0.0258 0.0125 1.0000
13.500 0.7064 0.08669 0.07864 0.0240 0.0120 1.0000
13.750 0.6990 0.09141 0.08349 0.0224 0.0117 1.0000
14.000 0.6932 0.09594 0.08812 0.0208 0.0117 1.0000
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