US1000ROOT (us1000root-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: US1000ROOT (us1000root-il) Reynolds number: 1,000,000 Max Cl/Cd: 45.95 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-us1000root-il-1000000-n5.txt Download as CSV file: xf-us1000root-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9822 0.08879 0.08461 -0.0164 1.0000 0.0011
-16.250 -0.9855 0.08487 0.08064 -0.0177 1.0000 0.0012
-16.000 -1.0046 0.07877 0.07442 -0.0198 1.0000 0.0011
-15.750 -1.0030 0.07567 0.07128 -0.0208 1.0000 0.0012
-15.500 -1.0049 0.07208 0.06764 -0.0219 1.0000 0.0012
-15.250 -1.0312 0.06531 0.06072 -0.0241 1.0000 0.0012
-15.000 -1.0448 0.06033 0.05563 -0.0256 1.0000 0.0012
-14.750 -1.0626 0.05492 0.05010 -0.0272 1.0000 0.0012
-14.500 -1.0624 0.05188 0.04700 -0.0280 1.0000 0.0012
-14.250 -1.0647 0.04859 0.04364 -0.0288 1.0000 0.0012
-14.000 -1.0790 0.04399 0.03891 -0.0298 1.0000 0.0012
-13.750 -1.0800 0.04104 0.03588 -0.0302 1.0000 0.0012
-13.500 -1.0795 0.03836 0.03314 -0.0306 1.0000 0.0012
-13.250 -1.0841 0.03527 0.02994 -0.0307 1.0000 0.0012
-13.000 -1.0892 0.03232 0.02689 -0.0304 1.0000 0.0012
-12.750 -1.0739 0.03139 0.02597 -0.0303 1.0000 0.0012
-12.500 -1.0760 0.02900 0.02347 -0.0295 1.0000 0.0013
-12.250 -1.0663 0.02772 0.02216 -0.0289 1.0000 0.0013
-12.000 -1.0678 0.02567 0.02002 -0.0275 1.0000 0.0013
-11.750 -1.0642 0.02415 0.01842 -0.0260 1.0000 0.0013
-11.500 -1.0577 0.02294 0.01715 -0.0245 1.0000 0.0013
-11.250 -1.0526 0.02174 0.01589 -0.0226 1.0000 0.0014
-10.750 -1.0357 0.01965 0.01370 -0.0189 0.9570 0.0014
-10.500 -0.9807 0.01827 0.01222 -0.0267 0.9371 0.0017
-10.250 -0.9112 0.01729 0.01114 -0.0367 0.9175 0.0017
-10.000 -0.8571 0.01666 0.01035 -0.0434 0.8893 0.0018
-9.750 -0.8226 0.01615 0.00973 -0.0460 0.8731 0.0019
-9.500 -0.7913 0.01560 0.00910 -0.0478 0.8611 0.0022
-9.250 -0.7643 0.01519 0.00862 -0.0485 0.8503 0.0023
-9.000 -0.7398 0.01477 0.00814 -0.0486 0.8410 0.0028
-8.750 -0.7179 0.01437 0.00769 -0.0481 0.8317 0.0036
-8.500 -0.7040 0.01363 0.00700 -0.0463 0.8217 0.0211
-8.000 -0.6632 0.01299 0.00629 -0.0442 0.8017 0.0310
-7.750 -0.6680 0.01169 0.00527 -0.0390 0.7921 0.0981
-7.500 -0.6623 0.01093 0.00469 -0.0351 0.7806 0.1351
-7.250 -0.6568 0.01027 0.00423 -0.0311 0.7684 0.1767
-7.000 -0.6365 0.01017 0.00408 -0.0296 0.7547 0.1795
-6.750 -0.6214 0.00985 0.00384 -0.0273 0.7414 0.2024
-6.500 -0.6024 0.00964 0.00365 -0.0256 0.7270 0.2181
-6.000 -0.5610 0.00940 0.00336 -0.0228 0.6911 0.2380
-5.750 -0.5404 0.00928 0.00322 -0.0213 0.6729 0.2478
-5.500 -0.5180 0.00924 0.00310 -0.0202 0.6525 0.2517
-5.250 -0.4957 0.00919 0.00298 -0.0190 0.6344 0.2557
-5.000 -0.4738 0.00914 0.00287 -0.0178 0.6136 0.2606
-4.750 -0.4510 0.00911 0.00278 -0.0168 0.5954 0.2659
-4.500 -0.4284 0.00909 0.00269 -0.0157 0.5755 0.2693
-4.250 -0.4057 0.00905 0.00259 -0.0146 0.5584 0.2734
-4.000 -0.3826 0.00902 0.00252 -0.0136 0.5418 0.2775
-3.750 -0.3589 0.00902 0.00245 -0.0127 0.5263 0.2817
-3.500 -0.3361 0.00899 0.00237 -0.0117 0.5099 0.2858
-3.250 -0.3127 0.00896 0.00231 -0.0107 0.4965 0.2904
-3.000 -0.2888 0.00895 0.00225 -0.0098 0.4845 0.2948
-2.750 -0.2654 0.00893 0.00219 -0.0089 0.4721 0.3002
-2.500 -0.2420 0.00891 0.00215 -0.0080 0.4589 0.3057
-2.250 -0.2176 0.00890 0.00210 -0.0072 0.4483 0.3107
-2.000 -0.1938 0.00887 0.00206 -0.0063 0.4394 0.3163
-1.750 -0.1698 0.00885 0.00203 -0.0055 0.4301 0.3221
-1.500 -0.1454 0.00884 0.00200 -0.0047 0.4214 0.3275
-1.250 -0.1216 0.00883 0.00197 -0.0039 0.4125 0.3340
-1.000 -0.0972 0.00883 0.00195 -0.0031 0.4022 0.3403
-0.750 -0.0735 0.00880 0.00193 -0.0022 0.3938 0.3485
-0.500 -0.0492 0.00880 0.00192 -0.0014 0.3858 0.3560
-0.250 -0.0250 0.00878 0.00191 -0.0006 0.3786 0.3637
0.000 -0.0008 0.00880 0.00191 0.0002 0.3707 0.3706
0.250 0.0235 0.00878 0.00191 0.0010 0.3638 0.3785
0.500 0.0477 0.00881 0.00192 0.0018 0.3557 0.3855
0.750 0.0719 0.00880 0.00193 0.0026 0.3486 0.3942
1.250 0.1200 0.00882 0.00197 0.0042 0.3341 0.4128
1.500 0.1438 0.00884 0.00200 0.0051 0.3276 0.4215
1.750 0.1682 0.00885 0.00203 0.0058 0.3223 0.4299
2.000 0.1923 0.00887 0.00206 0.0067 0.3164 0.4391
2.250 0.2160 0.00890 0.00211 0.0076 0.3106 0.4484
2.500 0.2403 0.00891 0.00215 0.0084 0.3058 0.4594
2.750 0.2638 0.00893 0.00220 0.0093 0.2999 0.4708
3.000 0.2872 0.00896 0.00226 0.0102 0.2946 0.4833
3.250 0.3105 0.00899 0.00232 0.0112 0.2872 0.4961
3.500 0.3276 0.00928 0.00244 0.0132 0.2476 0.5085
3.750 0.3489 0.00936 0.00252 0.0146 0.2356 0.5265
4.000 0.3712 0.00942 0.00261 0.0157 0.2271 0.5417
4.250 0.3885 0.00970 0.00278 0.0177 0.1965 0.5562
4.500 0.4023 0.01011 0.00303 0.0203 0.1549 0.5729
4.750 0.3922 0.01159 0.00397 0.0273 0.0027 0.5843
5.250 0.4336 0.01178 0.00430 0.0301 0.0023 0.6236
5.500 0.4538 0.01188 0.00448 0.0316 0.0023 0.6452
5.750 0.4737 0.01201 0.00470 0.0331 0.0021 0.6646
6.000 0.4922 0.01212 0.00489 0.0349 0.0021 0.6836
6.250 0.5100 0.01226 0.00511 0.0369 0.0021 0.7017
6.500 0.5280 0.01244 0.00537 0.0388 0.0020 0.7216
6.750 0.5465 0.01266 0.00567 0.0405 0.0019 0.7383
7.000 0.5657 0.01289 0.00598 0.0420 0.0019 0.7534
7.250 0.5847 0.01317 0.00632 0.0436 0.0019 0.7668
7.500 0.6038 0.01346 0.00669 0.0450 0.0019 0.7801
7.750 0.6234 0.01380 0.00709 0.0463 0.0019 0.7921
8.000 0.6436 0.01416 0.00751 0.0473 0.0018 0.8027
8.250 0.6653 0.01448 0.00786 0.0481 0.0019 0.8126
8.500 0.6850 0.01501 0.00849 0.0489 0.0018 0.8232
8.750 0.7060 0.01557 0.00912 0.0494 0.0018 0.8322
9.000 0.7276 0.01614 0.00976 0.0496 0.0018 0.8422
9.250 0.7544 0.01671 0.01040 0.0486 0.0018 0.8513
9.500 0.7812 0.01732 0.01109 0.0475 0.0018 0.8624
9.750 0.8032 0.01818 0.01206 0.0469 0.0018 0.8756
10.000 0.8274 0.01918 0.01322 0.0454 0.0018 0.8961
10.250 0.8851 0.02051 0.01476 0.0366 0.0018 0.9285
10.500 0.9492 0.02225 0.01660 0.0262 0.0018 0.9476
11.000 0.9661 0.02568 0.02017 0.0272 0.0018 1.0000
11.250 0.9680 0.02743 0.02199 0.0285 0.0018 1.0000
11.500 0.9653 0.02972 0.02437 0.0295 0.0018 1.0000
11.750 0.9688 0.03168 0.02638 0.0301 0.0018 1.0000
12.000 0.9674 0.03423 0.02901 0.0303 0.0018 1.0000
12.250 0.9673 0.03684 0.03169 0.0303 0.0018 1.0000
12.500 0.9639 0.03993 0.03486 0.0301 0.0018 1.0000
12.750 0.9571 0.04353 0.03855 0.0295 0.0019 1.0000
13.000 0.9544 0.04676 0.04185 0.0289 0.0018 1.0000
13.250 0.9527 0.04994 0.04512 0.0282 0.0019 1.0000
13.500 0.9461 0.05377 0.04903 0.0273 0.0019 1.0000
13.750 0.9396 0.05763 0.05297 0.0264 0.0019 1.0000
14.000 0.9333 0.06152 0.05692 0.0254 0.0019 1.0000
14.250 0.9340 0.06469 0.06015 0.0245 0.0019 1.0000
14.500 0.9271 0.06873 0.06425 0.0234 0.0019 1.0000
14.750 0.9253 0.07226 0.06785 0.0224 0.0019 1.0000
15.000 0.9206 0.07613 0.07178 0.0213 0.0019 1.0000
15.250 0.9177 0.07980 0.07551 0.0203 0.0019 1.0000
15.500 0.9175 0.08327 0.07902 0.0191 0.0019 1.0000
15.750 0.9158 0.08679 0.08261 0.0181 0.0019 1.0000
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