US1000ROOT (us1000root-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: US1000ROOT (us1000root-il) Reynolds number: 500,000 Max Cl/Cd: 49.84 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-us1000root-il-500000.txt Download as CSV file: xf-us1000root-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8743 0.08785 0.08300 -0.0210 1.0000 0.0054
-15.250 -0.8768 0.08449 0.07958 -0.0216 1.0000 0.0054
-15.000 -0.8798 0.08082 0.07586 -0.0225 1.0000 0.0055
-14.750 -0.8877 0.07659 0.07156 -0.0236 1.0000 0.0055
-14.500 -0.8886 0.07313 0.06803 -0.0247 1.0000 0.0055
-14.250 -0.8954 0.06900 0.06383 -0.0258 1.0000 0.0056
-14.000 -0.9027 0.06489 0.05965 -0.0270 1.0000 0.0055
-13.750 -0.9083 0.06100 0.05568 -0.0280 1.0000 0.0054
-13.500 -0.9152 0.05703 0.05161 -0.0291 1.0000 0.0055
-13.250 -0.9263 0.05261 0.04708 -0.0302 1.0000 0.0055
-13.000 -0.9373 0.04830 0.04266 -0.0311 1.0000 0.0056
-12.750 -0.9351 0.04565 0.03995 -0.0317 1.0000 0.0055
-12.500 -0.9495 0.04117 0.03533 -0.0324 1.0000 0.0056
-12.250 -0.9530 0.03812 0.03218 -0.0327 1.0000 0.0055
-12.000 -0.9570 0.03516 0.02912 -0.0326 1.0000 0.0056
-11.750 -0.9631 0.03225 0.02610 -0.0321 1.0000 0.0057
-11.500 -0.9619 0.03018 0.02394 -0.0313 1.0000 0.0057
-11.250 -0.9635 0.02808 0.02174 -0.0301 1.0000 0.0058
-10.750 -0.9629 0.02468 0.01817 -0.0266 1.0000 0.0059
-10.500 -0.9690 0.02285 0.01621 -0.0236 1.0000 0.0063
-10.250 -0.9644 0.02182 0.01512 -0.0212 1.0000 0.0064
-10.000 -0.9596 0.02092 0.01415 -0.0184 1.0000 0.0066
-9.750 -0.9539 0.02019 0.01337 -0.0155 1.0000 0.0068
-9.500 -0.9507 0.01948 0.01260 -0.0118 1.0000 0.0077
-9.250 -0.9463 0.01897 0.01203 -0.0081 1.0000 0.0081
-9.000 -0.9480 0.01849 0.01152 -0.0032 0.9998 0.0095
-8.750 -0.9213 0.01701 0.01013 -0.0047 0.9898 0.0341
-8.500 -0.9288 0.01385 0.00779 -0.0009 0.9520 0.1603
-8.250 -0.8914 0.01302 0.00717 -0.0037 0.9441 0.1991
-8.000 -0.8469 0.01251 0.00675 -0.0078 0.9370 0.2257
-7.750 -0.7960 0.01212 0.00639 -0.0130 0.9304 0.2423
-7.500 -0.7416 0.01180 0.00610 -0.0191 0.9235 0.2603
-7.250 -0.6853 0.01155 0.00579 -0.0255 0.9153 0.2705
-7.000 -0.6367 0.01143 0.00560 -0.0302 0.9042 0.2820
-6.750 -0.5995 0.01123 0.00540 -0.0326 0.8920 0.2912
-6.500 -0.5670 0.01115 0.00520 -0.0337 0.8797 0.2958
-6.250 -0.5404 0.01098 0.00501 -0.0336 0.8687 0.3011
-6.000 -0.5170 0.01090 0.00488 -0.0327 0.8573 0.3066
-5.750 -0.4948 0.01085 0.00474 -0.0315 0.8455 0.3115
-5.500 -0.4742 0.01067 0.00457 -0.0301 0.8344 0.3165
-5.250 -0.4522 0.01057 0.00443 -0.0288 0.8232 0.3214
-5.000 -0.4293 0.01050 0.00428 -0.0277 0.8121 0.3262
-4.750 -0.4100 0.01033 0.00413 -0.0259 0.7992 0.3317
-4.500 -0.3886 0.01024 0.00400 -0.0245 0.7865 0.3376
-4.250 -0.3674 0.01012 0.00384 -0.0231 0.7730 0.3431
-4.000 -0.3464 0.01001 0.00371 -0.0216 0.7590 0.3492
-3.750 -0.3243 0.00994 0.00358 -0.0203 0.7434 0.3556
-3.500 -0.3038 0.00983 0.00345 -0.0187 0.7275 0.3626
-3.000 -0.2608 0.00969 0.00322 -0.0159 0.6938 0.3773
-2.750 -0.2387 0.00967 0.00313 -0.0146 0.6751 0.3850
-2.500 -0.2178 0.00960 0.00304 -0.0131 0.6565 0.3930
-2.250 -0.1961 0.00959 0.00296 -0.0118 0.6378 0.4012
-2.000 -0.1748 0.00956 0.00289 -0.0103 0.6198 0.4101
-1.750 -0.1533 0.00953 0.00283 -0.0090 0.6012 0.4190
-1.250 -0.1103 0.00952 0.00274 -0.0062 0.5652 0.4387
-1.000 -0.0885 0.00952 0.00270 -0.0049 0.5493 0.4484
-0.500 -0.0446 0.00952 0.00266 -0.0024 0.5197 0.4695
-0.250 -0.0227 0.00951 0.00265 -0.0011 0.5063 0.4808
0.000 -0.0008 0.00951 0.00264 0.0002 0.4929 0.4930
0.250 0.0211 0.00951 0.00265 0.0015 0.4806 0.5063
0.500 0.0431 0.00952 0.00266 0.0027 0.4696 0.5198
0.750 0.0648 0.00953 0.00268 0.0040 0.4589 0.5340
1.000 0.0870 0.00952 0.00270 0.0053 0.4484 0.5492
1.250 0.1087 0.00952 0.00274 0.0066 0.4387 0.5651
1.750 0.1518 0.00954 0.00284 0.0093 0.4192 0.6004
2.000 0.1733 0.00956 0.00289 0.0107 0.4101 0.6190
2.250 0.1945 0.00959 0.00296 0.0121 0.4014 0.6377
2.500 0.2161 0.00960 0.00304 0.0135 0.3930 0.6563
2.750 0.2369 0.00967 0.00314 0.0150 0.3851 0.6753
3.000 0.2590 0.00969 0.00323 0.0163 0.3774 0.6939
3.500 0.3017 0.00982 0.00346 0.0192 0.3625 0.7281
3.750 0.3225 0.00994 0.00359 0.0207 0.3557 0.7435
4.000 0.3445 0.01000 0.00372 0.0220 0.3491 0.7588
4.250 0.3643 0.01009 0.00379 0.0237 0.3346 0.7730
4.500 0.3849 0.01020 0.00392 0.0253 0.3281 0.7866
4.750 0.4044 0.01030 0.00400 0.0271 0.3138 0.7994
5.000 0.4238 0.01042 0.00410 0.0288 0.3008 0.8120
5.250 0.4443 0.01053 0.00422 0.0304 0.2886 0.8234
5.500 0.4648 0.01065 0.00436 0.0319 0.2799 0.8349
5.750 0.4845 0.01080 0.00448 0.0335 0.2666 0.8463
6.000 0.5061 0.01089 0.00460 0.0348 0.2586 0.8579
6.500 0.5508 0.01127 0.00491 0.0366 0.2247 0.8824
6.750 0.5801 0.01164 0.00519 0.0358 0.1930 0.8953
7.000 0.6147 0.01250 0.00579 0.0332 0.1378 0.9084
7.250 0.6488 0.01494 0.00765 0.0290 0.0079 0.9226
7.500 0.7053 0.01550 0.00825 0.0224 0.0067 0.9307
7.750 0.7570 0.01611 0.00894 0.0169 0.0063 0.9384
8.000 0.8029 0.01678 0.00969 0.0125 0.0061 0.9464
8.250 0.8431 0.01740 0.01038 0.0094 0.0061 0.9559
8.500 0.8700 0.01811 0.01118 0.0088 0.0060 0.9816
8.750 0.8988 0.01897 0.01211 0.0077 0.0060 0.9984
9.000 0.9128 0.01961 0.01281 0.0093 0.0060 1.0000
9.250 0.9149 0.02016 0.01340 0.0133 0.0060 1.0000
9.500 0.9172 0.02091 0.01421 0.0169 0.0060 1.0000
9.750 0.9196 0.02181 0.01519 0.0202 0.0060 1.0000
10.000 0.9205 0.02296 0.01642 0.0231 0.0060 1.0000
10.250 0.9214 0.02428 0.01782 0.0256 0.0060 1.0000
10.500 0.9236 0.02569 0.01930 0.0276 0.0060 1.0000
10.750 0.9250 0.02729 0.02098 0.0293 0.0060 1.0000
11.000 0.9223 0.02939 0.02317 0.0308 0.0060 1.0000
11.250 0.9198 0.03169 0.02557 0.0318 0.0060 1.0000
11.500 0.9095 0.03494 0.02893 0.0325 0.0061 1.0000
11.750 0.9065 0.03776 0.03184 0.0326 0.0061 1.0000
12.000 0.9025 0.04084 0.03501 0.0324 0.0061 1.0000
12.250 0.8970 0.04424 0.03849 0.0320 0.0061 1.0000
12.500 0.8876 0.04815 0.04250 0.0313 0.0062 1.0000
12.750 0.8825 0.05165 0.04608 0.0307 0.0062 1.0000
13.000 0.8775 0.05518 0.04968 0.0300 0.0062 1.0000
13.250 0.8789 0.05810 0.05266 0.0293 0.0063 1.0000
13.500 0.8756 0.06154 0.05617 0.0286 0.0063 1.0000
13.750 0.8732 0.06491 0.05960 0.0280 0.0063 1.0000
14.000 0.8727 0.06806 0.06281 0.0272 0.0064 1.0000
14.250 0.8739 0.07113 0.06593 0.0264 0.0064 1.0000
14.500 0.8743 0.07415 0.06902 0.0259 0.0065 1.0000
14.750 0.8772 0.07686 0.07181 0.0255 0.0067 1.0000
15.000 0.8805 0.07936 0.07437 0.0254 0.0068 1.0000
15.250 0.8911 0.08012 0.07518 0.0274 0.0074 1.0000
15.500 0.8927 0.08344 0.07855 0.0259 0.0072 1.0000
15.750 0.9092 0.08307 0.07822 0.0291 0.0079 1.0000
16.000 0.9176 0.08478 0.07997 0.0298 0.0081 1.0000
16.250 0.9456 0.08336 0.07848 0.0335 0.0089 1.0000
16.500 0.7386 0.09565 0.09149 0.0316 0.0079 1.0000
16.750 0.7389 0.09858 0.09448 0.0307 0.0078 1.0000
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