US1000ROOT (us1000root-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: US1000ROOT (us1000root-il) Reynolds number: 200,000 Max Cl/Cd: 44.25 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-us1000root-il-200000-n5.txt Download as CSV file: xf-us1000root-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8075 0.09482 0.08862 -0.0198 1.0000 0.0058
-15.000 -0.8184 0.08957 0.08329 -0.0217 1.0000 0.0059
-14.750 -0.8337 0.08374 0.07737 -0.0239 1.0000 0.0063
-14.500 -0.8378 0.07967 0.07316 -0.0253 1.0000 0.0060
-14.250 -0.8517 0.07429 0.06767 -0.0272 1.0000 0.0062
-14.000 -0.8579 0.07009 0.06337 -0.0287 1.0000 0.0062
-13.750 -0.8629 0.06612 0.05929 -0.0299 1.0000 0.0060
-13.500 -0.8705 0.06190 0.05494 -0.0313 1.0000 0.0059
-13.250 -0.8858 0.05681 0.04973 -0.0328 1.0000 0.0063
-13.000 -0.8951 0.05267 0.04546 -0.0340 1.0000 0.0067
-12.750 -0.8919 0.05013 0.04281 -0.0345 1.0000 0.0060
-12.500 -0.9046 0.04586 0.03842 -0.0353 1.0000 0.0070
-12.250 -0.9054 0.04308 0.03551 -0.0356 1.0000 0.0066
-12.000 -0.9090 0.04015 0.03247 -0.0357 1.0000 0.0072
-11.750 -0.9118 0.03747 0.02966 -0.0354 1.0000 0.0078
-11.500 -0.9120 0.03521 0.02729 -0.0348 1.0000 0.0085
-11.250 -0.9129 0.03306 0.02507 -0.0339 1.0000 0.0093
-11.000 -0.9107 0.03130 0.02323 -0.0328 1.0000 0.0100
-10.750 -0.9087 0.02967 0.02152 -0.0313 1.0000 0.0121
-10.500 -0.9161 0.02758 0.01944 -0.0289 1.0000 0.0209
-10.250 -0.9158 0.02617 0.01797 -0.0265 1.0000 0.0271
-10.000 -0.9204 0.02468 0.01647 -0.0232 1.0000 0.0357
-9.750 -0.9406 0.02273 0.01477 -0.0176 1.0000 0.0748
-9.500 -0.9636 0.02102 0.01342 -0.0106 1.0000 0.1233
-9.250 -0.9702 0.02023 0.01275 -0.0052 1.0000 0.1445
-9.000 -0.9788 0.01953 0.01226 0.0007 1.0000 0.1718
-8.750 -0.9561 0.01875 0.01165 0.0004 0.9908 0.2073
-8.500 -0.9322 0.01824 0.01115 0.0005 0.9667 0.2257
-8.250 -0.9007 0.01779 0.01072 -0.0009 0.9513 0.2429
-8.000 -0.8626 0.01740 0.01026 -0.0034 0.9406 0.2553
-7.750 -0.8213 0.01706 0.00982 -0.0066 0.9310 0.2677
-7.500 -0.7777 0.01665 0.00937 -0.0103 0.9220 0.2758
-7.250 -0.7295 0.01630 0.00888 -0.0148 0.9140 0.2833
-7.000 -0.6855 0.01594 0.00848 -0.0186 0.9038 0.2899
-6.750 -0.6419 0.01566 0.00806 -0.0222 0.8932 0.2967
-6.500 -0.6017 0.01534 0.00771 -0.0251 0.8825 0.3021
-6.250 -0.5649 0.01511 0.00738 -0.0271 0.8709 0.3078
-6.000 -0.5350 0.01492 0.00711 -0.0277 0.8585 0.3127
-5.750 -0.5087 0.01473 0.00690 -0.0276 0.8462 0.3175
-5.500 -0.4833 0.01459 0.00668 -0.0272 0.8339 0.3229
-5.250 -0.4592 0.01444 0.00646 -0.0265 0.8215 0.3275
-5.000 -0.4366 0.01428 0.00627 -0.0254 0.8090 0.3325
-4.750 -0.4138 0.01415 0.00608 -0.0244 0.7959 0.3383
-4.500 -0.3920 0.01400 0.00590 -0.0232 0.7820 0.3437
-4.250 -0.3702 0.01387 0.00572 -0.0219 0.7678 0.3496
-4.000 -0.3479 0.01375 0.00553 -0.0207 0.7524 0.3556
-3.750 -0.3266 0.01361 0.00537 -0.0193 0.7361 0.3612
-3.500 -0.3045 0.01351 0.00519 -0.0181 0.7192 0.3680
-3.250 -0.2828 0.01339 0.00504 -0.0168 0.7018 0.3747
-3.000 -0.2609 0.01331 0.00489 -0.0155 0.6839 0.3825
-2.750 -0.2392 0.01323 0.00476 -0.0142 0.6662 0.3896
-2.500 -0.2172 0.01317 0.00462 -0.0129 0.6477 0.3976
-2.250 -0.1957 0.01311 0.00451 -0.0116 0.6294 0.4048
-2.000 -0.1737 0.01308 0.00440 -0.0103 0.6115 0.4134
-1.750 -0.1524 0.01303 0.00432 -0.0089 0.5945 0.4219
-1.500 -0.1306 0.01300 0.00425 -0.0076 0.5782 0.4311
-1.250 -0.1091 0.01298 0.00418 -0.0063 0.5623 0.4407
-1.000 -0.0876 0.01296 0.00413 -0.0050 0.5471 0.4502
-0.500 -0.0441 0.01294 0.00406 -0.0024 0.5187 0.4702
-0.250 -0.0224 0.01293 0.00404 -0.0011 0.5056 0.4811
0.000 -0.0008 0.01293 0.00404 0.0002 0.4932 0.4931
0.250 0.0209 0.01293 0.00405 0.0015 0.4815 0.5056
0.500 0.0426 0.01295 0.00406 0.0028 0.4704 0.5185
1.000 0.0861 0.01296 0.00413 0.0053 0.4502 0.5467
1.250 0.1075 0.01298 0.00418 0.0067 0.4407 0.5623
1.500 0.1290 0.01300 0.00425 0.0080 0.4310 0.5782
1.750 0.1507 0.01303 0.00432 0.0093 0.4219 0.5945
2.000 0.1719 0.01308 0.00441 0.0107 0.4135 0.6117
2.250 0.1940 0.01311 0.00452 0.0119 0.4049 0.6295
2.500 0.2155 0.01317 0.00463 0.0133 0.3976 0.6478
2.750 0.2375 0.01323 0.00476 0.0145 0.3897 0.6658
3.000 0.2591 0.01331 0.00490 0.0159 0.3827 0.6838
3.250 0.2810 0.01339 0.00505 0.0172 0.3748 0.7017
3.500 0.3026 0.01351 0.00521 0.0185 0.3682 0.7193
3.750 0.3247 0.01361 0.00538 0.0198 0.3614 0.7365
4.000 0.3461 0.01375 0.00554 0.0211 0.3556 0.7523
4.250 0.3683 0.01386 0.00573 0.0223 0.3497 0.7678
4.500 0.3899 0.01400 0.00591 0.0236 0.3437 0.7821
4.750 0.4119 0.01415 0.00610 0.0248 0.3385 0.7959
5.000 0.4347 0.01427 0.00629 0.0259 0.3324 0.8088
5.250 0.4572 0.01443 0.00648 0.0269 0.3275 0.8217
5.500 0.4798 0.01454 0.00666 0.0279 0.3183 0.8342
5.750 0.5023 0.01468 0.00681 0.0289 0.3070 0.8468
6.000 0.5276 0.01484 0.00699 0.0292 0.2984 0.8593
6.250 0.5561 0.01501 0.00720 0.0288 0.2860 0.8720
6.500 0.5907 0.01523 0.00748 0.0271 0.2757 0.8844
6.750 0.6305 0.01556 0.00780 0.0241 0.2563 0.8959
7.000 0.6725 0.01599 0.00818 0.0205 0.2307 0.9066
7.250 0.7164 0.01651 0.00865 0.0166 0.2080 0.9168
7.500 0.7607 0.01719 0.00925 0.0124 0.1754 0.9261
7.750 0.7806 0.01966 0.01101 0.0109 0.0649 0.9401
8.000 0.7989 0.02164 0.01275 0.0104 0.0076 0.9611
8.250 0.8232 0.02228 0.01345 0.0103 0.0075 0.9924
8.500 0.8384 0.02307 0.01426 0.0115 0.0063 1.0000
8.750 0.8400 0.02362 0.01484 0.0155 0.0060 1.0000
9.000 0.8438 0.02426 0.01554 0.0188 0.0058 1.0000
9.250 0.8493 0.02496 0.01630 0.0216 0.0058 1.0000
9.500 0.8543 0.02582 0.01723 0.0242 0.0058 1.0000
9.750 0.8590 0.02683 0.01831 0.0266 0.0056 1.0000
10.000 0.8631 0.02800 0.01957 0.0286 0.0055 1.0000
10.250 0.8670 0.02930 0.02100 0.0304 0.0053 1.0000
10.500 0.8719 0.03066 0.02245 0.0319 0.0054 1.0000
10.750 0.8758 0.03221 0.02408 0.0331 0.0053 1.0000
11.000 0.8773 0.03409 0.02606 0.0341 0.0053 1.0000
11.250 0.8783 0.03615 0.02824 0.0349 0.0052 1.0000
11.500 0.8749 0.03880 0.03102 0.0353 0.0050 1.0000
11.750 0.8745 0.04134 0.03367 0.0354 0.0051 1.0000
12.000 0.8728 0.04415 0.03659 0.0352 0.0051 1.0000
12.250 0.8696 0.04729 0.03985 0.0347 0.0051 1.0000
12.500 0.8626 0.05100 0.04369 0.0339 0.0051 1.0000
12.750 0.8520 0.05530 0.04813 0.0327 0.0049 1.0000
13.000 0.8474 0.05895 0.05188 0.0317 0.0049 1.0000
13.250 0.8392 0.06320 0.05625 0.0304 0.0050 1.0000
13.500 0.8289 0.06785 0.06102 0.0289 0.0049 1.0000
13.750 0.8188 0.07256 0.06584 0.0273 0.0049 1.0000
14.000 0.8111 0.07703 0.07040 0.0258 0.0049 1.0000
14.250 0.8066 0.08113 0.07459 0.0244 0.0050 1.0000
14.500 0.7979 0.08587 0.07942 0.0227 0.0049 1.0000
14.750 0.7915 0.09035 0.08399 0.0211 0.0049 1.0000
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