US1000ROOT (us1000root-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: US1000ROOT (us1000root-il) Reynolds number: 500,000 Max Cl/Cd: 43.15 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-us1000root-il-500000-n5.txt Download as CSV file: xf-us1000root-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8909 0.09029 0.08536 -0.0182 1.0000 0.0023
-15.500 -0.8957 0.08611 0.08111 -0.0197 1.0000 0.0023
-15.250 -0.9095 0.08073 0.07563 -0.0214 1.0000 0.0023
-15.000 -0.9162 0.07640 0.07122 -0.0228 1.0000 0.0024
-14.750 -0.9300 0.07115 0.06587 -0.0245 1.0000 0.0024
-14.500 -0.9380 0.06682 0.06146 -0.0259 1.0000 0.0024
-14.250 -0.9480 0.06229 0.05682 -0.0273 1.0000 0.0024
-14.000 -0.9517 0.05864 0.05310 -0.0283 1.0000 0.0024
-13.750 -0.9582 0.05471 0.04909 -0.0294 1.0000 0.0024
-13.500 -0.9675 0.05053 0.04480 -0.0305 1.0000 0.0023
-13.250 -0.9782 0.04629 0.04043 -0.0314 1.0000 0.0024
-13.000 -0.9869 0.04243 0.03646 -0.0321 1.0000 0.0024
-12.750 -0.9792 0.04054 0.03451 -0.0323 1.0000 0.0023
-12.500 -0.9927 0.03650 0.03032 -0.0326 1.0000 0.0025
-12.250 -0.9876 0.03454 0.02829 -0.0324 1.0000 0.0024
-12.000 -0.9918 0.03184 0.02549 -0.0318 1.0000 0.0025
-11.750 -0.9935 0.02957 0.02312 -0.0309 1.0000 0.0025
-11.500 -0.9936 0.02762 0.02108 -0.0297 1.0000 0.0026
-11.250 -0.9891 0.02615 0.01954 -0.0283 1.0000 0.0026
-11.000 -0.9833 0.02489 0.01821 -0.0268 1.0000 0.0026
-10.750 -0.9786 0.02365 0.01690 -0.0249 1.0000 0.0027
-10.500 -0.9758 0.02242 0.01559 -0.0226 1.0000 0.0030
-10.250 -0.9684 0.02156 0.01469 -0.0204 1.0000 0.0030
-10.000 -0.9609 0.02082 0.01389 -0.0179 1.0000 0.0031
-9.750 -0.9460 0.02011 0.01313 -0.0167 0.9992 0.0032
-9.500 -0.9283 0.01918 0.01212 -0.0159 0.9510 0.0037
-9.250 -0.8739 0.01825 0.01112 -0.0226 0.9330 0.0047
-9.000 -0.8172 0.01706 0.00994 -0.0302 0.9187 0.0177
-8.750 -0.7743 0.01477 0.00796 -0.0367 0.9023 0.0946
-8.250 -0.7133 0.01290 0.00640 -0.0408 0.8725 0.1709
-8.000 -0.6944 0.01237 0.00600 -0.0398 0.8595 0.2050
-7.750 -0.6731 0.01210 0.00574 -0.0388 0.8487 0.2201
-7.500 -0.6517 0.01190 0.00552 -0.0377 0.8385 0.2290
-7.250 -0.6314 0.01172 0.00532 -0.0364 0.8282 0.2401
-7.000 -0.6132 0.01155 0.00516 -0.0345 0.8178 0.2511
-6.750 -0.5944 0.01140 0.00499 -0.0328 0.8076 0.2579
-6.500 -0.5742 0.01129 0.00481 -0.0313 0.7960 0.2618
-6.250 -0.5526 0.01118 0.00464 -0.0300 0.7846 0.2666
-6.000 -0.5324 0.01104 0.00447 -0.0285 0.7725 0.2714
-5.750 -0.5116 0.01092 0.00431 -0.0271 0.7586 0.2767
-5.500 -0.4898 0.01084 0.00416 -0.0258 0.7440 0.2807
-5.250 -0.4688 0.01074 0.00399 -0.0244 0.7278 0.2843
-5.000 -0.4479 0.01065 0.00384 -0.0230 0.7115 0.2885
-4.750 -0.4266 0.01059 0.00370 -0.0216 0.6926 0.2933
-4.500 -0.4047 0.01053 0.00356 -0.0203 0.6744 0.2975
-4.250 -0.3839 0.01047 0.00343 -0.0188 0.6550 0.3019
-4.000 -0.3623 0.01043 0.00332 -0.0175 0.6367 0.3067
-3.500 -0.3191 0.01035 0.00311 -0.0149 0.5982 0.3173
-3.250 -0.2970 0.01033 0.00302 -0.0137 0.5807 0.3230
-3.000 -0.2748 0.01031 0.00294 -0.0125 0.5639 0.3282
-2.750 -0.2530 0.01029 0.00287 -0.0113 0.5471 0.3341
-2.500 -0.2302 0.01029 0.00280 -0.0102 0.5315 0.3401
-2.250 -0.2081 0.01026 0.00274 -0.0090 0.5166 0.3461
-2.000 -0.1852 0.01025 0.00269 -0.0079 0.5032 0.3533
-1.750 -0.1626 0.01023 0.00264 -0.0068 0.4901 0.3603
-1.500 -0.1396 0.01022 0.00261 -0.0058 0.4772 0.3682
-1.250 -0.1169 0.01020 0.00257 -0.0047 0.4655 0.3759
-1.000 -0.0935 0.01021 0.00255 -0.0038 0.4554 0.3836
-0.750 -0.0706 0.01019 0.00253 -0.0027 0.4455 0.3911
-0.500 -0.0468 0.01020 0.00252 -0.0019 0.4360 0.3991
-0.250 -0.0240 0.01019 0.00251 -0.0008 0.4270 0.4077
0.000 -0.0008 0.01019 0.00251 0.0002 0.4166 0.4168
0.250 0.0225 0.01019 0.00251 0.0012 0.4075 0.4270
0.750 0.0691 0.01019 0.00253 0.0031 0.3913 0.4453
1.000 0.0920 0.01021 0.00255 0.0041 0.3837 0.4553
1.250 0.1154 0.01020 0.00258 0.0051 0.3759 0.4653
1.500 0.1382 0.01023 0.00261 0.0061 0.3684 0.4764
1.750 0.1613 0.01023 0.00265 0.0071 0.3605 0.4891
2.000 0.1838 0.01026 0.00269 0.0083 0.3532 0.5022
2.250 0.2065 0.01026 0.00274 0.0093 0.3465 0.5165
2.500 0.2286 0.01029 0.00281 0.0106 0.3400 0.5313
2.750 0.2512 0.01028 0.00287 0.0116 0.3342 0.5475
3.000 0.2731 0.01031 0.00295 0.0129 0.3283 0.5642
3.250 0.2952 0.01033 0.00303 0.0141 0.3230 0.5807
3.500 0.3171 0.01035 0.00312 0.0154 0.3169 0.5998
4.000 0.3605 0.01044 0.00333 0.0179 0.3049 0.6359
4.250 0.3793 0.01056 0.00343 0.0197 0.2859 0.6546
4.500 0.4001 0.01063 0.00356 0.0212 0.2808 0.6739
4.750 0.4182 0.01082 0.00370 0.0231 0.2568 0.6918
5.000 0.4361 0.01102 0.00386 0.0250 0.2370 0.7095
5.250 0.4543 0.01122 0.00403 0.0269 0.2182 0.7267
5.500 0.4724 0.01142 0.00423 0.0288 0.2016 0.7432
5.750 0.4744 0.01232 0.00475 0.0333 0.1280 0.7580
6.000 0.4899 0.01259 0.00501 0.0356 0.1148 0.7718
6.250 0.4750 0.01403 0.00605 0.0431 0.0042 0.7852
6.500 0.4929 0.01426 0.00633 0.0449 0.0038 0.7980
6.750 0.5107 0.01451 0.00666 0.0467 0.0034 0.8103
7.000 0.5300 0.01477 0.00698 0.0481 0.0033 0.8208
7.250 0.5495 0.01506 0.00736 0.0495 0.0031 0.8324
7.500 0.5700 0.01537 0.00774 0.0505 0.0030 0.8441
7.750 0.5915 0.01572 0.00818 0.0512 0.0029 0.8556
8.000 0.6179 0.01612 0.00868 0.0508 0.0029 0.8683
8.250 0.6510 0.01649 0.00913 0.0489 0.0029 0.8813
8.500 0.6926 0.01711 0.00991 0.0450 0.0028 0.8961
8.750 0.7463 0.01787 0.01080 0.0384 0.0028 0.9094
9.000 0.8029 0.01881 0.01186 0.0311 0.0028 0.9231
9.250 0.8586 0.01990 0.01305 0.0238 0.0027 0.9380
9.750 0.9102 0.02222 0.01553 0.0209 0.0027 1.0000
10.000 0.9129 0.02332 0.01670 0.0235 0.0027 1.0000
10.250 0.9162 0.02454 0.01798 0.0257 0.0027 1.0000
10.500 0.9204 0.02583 0.01933 0.0274 0.0027 1.0000
10.750 0.9231 0.02736 0.02093 0.0290 0.0027 1.0000
11.000 0.9235 0.02921 0.02286 0.0304 0.0027 1.0000
11.250 0.9241 0.03123 0.02495 0.0314 0.0027 1.0000
11.500 0.9190 0.03395 0.02778 0.0320 0.0027 1.0000
11.750 0.9194 0.03637 0.03027 0.0322 0.0027 1.0000
12.000 0.9182 0.03910 0.03309 0.0321 0.0027 1.0000
12.250 0.9151 0.04219 0.03627 0.0318 0.0027 1.0000
12.500 0.9080 0.04587 0.04004 0.0312 0.0027 1.0000
12.750 0.8972 0.05008 0.04437 0.0303 0.0027 1.0000
13.000 0.8959 0.05328 0.04763 0.0295 0.0027 1.0000
13.250 0.8885 0.05724 0.05168 0.0285 0.0027 1.0000
13.500 0.8807 0.06134 0.05587 0.0274 0.0027 1.0000
13.750 0.8741 0.06536 0.05997 0.0264 0.0027 1.0000
14.000 0.8687 0.06926 0.06393 0.0253 0.0027 1.0000
14.250 0.8672 0.07275 0.06748 0.0242 0.0027 1.0000
14.500 0.8624 0.07667 0.07148 0.0231 0.0027 1.0000
14.750 0.8588 0.08043 0.07529 0.0220 0.0027 1.0000
15.000 0.8572 0.08401 0.07893 0.0210 0.0027 1.0000
15.250 0.8555 0.08753 0.08250 0.0200 0.0027 1.0000
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