US1000ROOT (us1000root-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: US1000ROOT (us1000root-il) Reynolds number: 50,000 Max Cl/Cd: 24.69 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-us1000root-il-50000-n5.txt Download as CSV file: xf-us1000root-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6170 0.08981 0.08113 -0.0230 1.0000 0.2551
-11.250 -0.6549 0.07789 0.06919 -0.0264 1.0000 0.2687
-10.750 -0.6958 0.06647 0.05776 -0.0289 1.0000 0.2839
-10.500 -0.6709 0.06662 0.05780 -0.0276 1.0000 0.2872
-10.250 -0.7841 0.05332 0.04462 -0.0284 1.0000 0.2992
-10.000 -0.7771 0.05191 0.04314 -0.0270 1.0000 0.3039
-9.750 -0.8587 0.04630 0.03751 -0.0190 1.0000 0.3098
-9.500 -0.8487 0.04535 0.03649 -0.0169 1.0000 0.3143
-9.250 -0.8407 0.04432 0.03538 -0.0147 1.0000 0.3190
-9.000 -0.8686 0.04178 0.03269 -0.0089 1.0000 0.3245
-8.750 -0.8543 0.04107 0.03193 -0.0071 1.0000 0.3291
-8.500 -0.8456 0.04023 0.03103 -0.0046 1.0000 0.3342
-8.250 -0.8630 0.03839 0.02900 0.0007 1.0000 0.3400
-8.000 -0.8439 0.03800 0.02863 0.0021 1.0000 0.3443
-7.750 -0.8384 0.03724 0.02780 0.0051 1.0000 0.3495
-7.500 -0.8514 0.03588 0.02624 0.0104 1.0000 0.3551
-7.250 -0.8350 0.03562 0.02597 0.0122 1.0000 0.3594
-7.000 -0.8315 0.03496 0.02524 0.0156 1.0000 0.3644
-6.750 -0.8375 0.03396 0.02403 0.0200 1.0000 0.3700
-6.500 -0.8237 0.03369 0.02378 0.0221 1.0000 0.3744
-6.250 -0.8183 0.03312 0.02312 0.0251 1.0000 0.3798
-6.000 -0.7937 0.03242 0.02225 0.0243 0.9931 0.3865
-5.750 -0.7541 0.03196 0.02171 0.0214 0.9816 0.3939
-5.500 -0.7190 0.03128 0.02085 0.0190 0.9687 0.4016
-5.250 -0.6795 0.03080 0.02028 0.0161 0.9570 0.4093
-5.000 -0.6423 0.03022 0.01959 0.0137 0.9448 0.4172
-4.750 -0.6048 0.02972 0.01899 0.0113 0.9326 0.4256
-4.500 -0.5646 0.02927 0.01847 0.0087 0.9211 0.4339
-4.250 -0.5255 0.02869 0.01775 0.0060 0.9100 0.4439
-4.000 -0.4778 0.02830 0.01737 0.0023 0.9003 0.4530
-3.750 -0.4376 0.02789 0.01690 -0.0003 0.8878 0.4628
-3.500 -0.4012 0.02746 0.01640 -0.0021 0.8746 0.4737
-3.250 -0.3623 0.02717 0.01612 -0.0041 0.8611 0.4834
-3.000 -0.3270 0.02687 0.01580 -0.0054 0.8467 0.4940
-2.750 -0.2954 0.02658 0.01548 -0.0060 0.8315 0.5053
-2.500 -0.2663 0.02630 0.01515 -0.0062 0.8157 0.5173
-2.250 -0.2350 0.02612 0.01500 -0.0065 0.7998 0.5282
-2.000 -0.2061 0.02591 0.01480 -0.0063 0.7837 0.5402
-1.750 -0.1791 0.02571 0.01459 -0.0058 0.7673 0.5525
-1.500 -0.1558 0.02555 0.01444 -0.0047 0.7498 0.5652
-1.250 -0.1313 0.02539 0.01429 -0.0038 0.7328 0.5787
-1.000 -0.1058 0.02525 0.01415 -0.0029 0.7161 0.5927
-0.750 -0.0800 0.02512 0.01403 -0.0021 0.6997 0.6070
-0.500 -0.0537 0.02504 0.01394 -0.0014 0.6837 0.6218
-0.250 -0.0273 0.02498 0.01389 -0.0006 0.6678 0.6370
0.000 -0.0007 0.02496 0.01388 0.0001 0.6523 0.6523
0.250 0.0259 0.02498 0.01389 0.0009 0.6369 0.6678
0.500 0.0523 0.02504 0.01395 0.0017 0.6219 0.6837
0.750 0.0785 0.02512 0.01403 0.0024 0.6071 0.6997
1.000 0.1044 0.02525 0.01416 0.0032 0.5927 0.7162
1.250 0.1298 0.02539 0.01429 0.0040 0.5787 0.7328
1.500 0.1544 0.02554 0.01443 0.0050 0.5651 0.7498
1.750 0.1776 0.02570 0.01460 0.0061 0.5525 0.7675
2.000 0.2049 0.02591 0.01481 0.0066 0.5402 0.7838
2.250 0.2338 0.02611 0.01500 0.0067 0.5284 0.7999
2.500 0.2650 0.02630 0.01516 0.0064 0.5172 0.8158
2.750 0.2942 0.02657 0.01548 0.0063 0.5053 0.8316
3.000 0.3260 0.02687 0.01581 0.0056 0.4941 0.8468
3.250 0.3615 0.02716 0.01613 0.0043 0.4835 0.8612
3.500 0.4004 0.02746 0.01641 0.0023 0.4737 0.8747
3.750 0.4371 0.02788 0.01692 0.0004 0.4628 0.8879
4.000 0.4772 0.02829 0.01739 -0.0021 0.4530 0.9003
4.250 0.5247 0.02867 0.01776 -0.0058 0.4438 0.9102
4.500 0.5640 0.02926 0.01849 -0.0085 0.4339 0.9212
4.750 0.6041 0.02970 0.01901 -0.0112 0.4256 0.9327
5.000 0.6418 0.03021 0.01962 -0.0136 0.4171 0.9449
5.250 0.6788 0.03078 0.02030 -0.0160 0.4092 0.9572
5.500 0.7183 0.03127 0.02088 -0.0188 0.4015 0.9689
5.750 0.7535 0.03194 0.02175 -0.0212 0.3936 0.9818
6.000 0.7930 0.03241 0.02230 -0.0242 0.3865 0.9932
6.250 0.8174 0.03310 0.02316 -0.0248 0.3797 1.0000
6.500 0.8229 0.03368 0.02384 -0.0218 0.3744 1.0000
6.750 0.8366 0.03396 0.02410 -0.0198 0.3700 1.0000
7.000 0.8310 0.03494 0.02528 -0.0154 0.3644 1.0000
7.250 0.8345 0.03560 0.02602 -0.0120 0.3593 1.0000
7.500 0.8503 0.03590 0.02634 -0.0101 0.3552 1.0000
7.750 0.8383 0.03721 0.02785 -0.0050 0.3494 1.0000
8.000 0.8439 0.03799 0.02869 -0.0020 0.3443 1.0000
8.250 0.8636 0.03836 0.02905 -0.0006 0.3400 1.0000
8.500 0.8460 0.04023 0.03112 0.0047 0.3343 1.0000
8.750 0.8543 0.04109 0.03205 0.0072 0.3291 1.0000
9.000 0.8706 0.04172 0.03273 0.0089 0.3246 1.0000
9.250 0.8415 0.04432 0.03550 0.0147 0.3191 1.0000
9.500 0.8486 0.04541 0.03666 0.0171 0.3143 1.0000
9.750 0.8654 0.04612 0.03744 0.0185 0.3101 1.0000
10.000 0.7788 0.05190 0.04325 0.0270 0.3040 1.0000
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Polar data table (+)
Polar graphs
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