LA2573A (la2573a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LA2573A (la2573a-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.83 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-la2573a-il-1000000.txt Download as CSV file: xf-la2573a-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: LA2573A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4967 0.11096 0.10753 0.0232 0.4537 0.0275
-10.000 -0.5297 0.09819 0.09479 0.0141 0.4550 0.0291
-9.750 -0.5427 0.09120 0.08783 0.0104 0.4543 0.0293
-9.500 -0.5384 0.08845 0.08507 0.0094 0.4527 0.0295
-9.250 -0.5371 0.08504 0.08167 0.0077 0.4513 0.0296
-9.000 -0.5411 0.08079 0.07744 0.0049 0.4500 0.0297
-8.750 -0.5651 0.07386 0.07052 -0.0011 0.4495 0.0297
-8.500 -0.6871 0.04930 0.04550 -0.0049 0.4538 0.0290
-8.250 -0.6807 0.04722 0.04333 -0.0038 0.4519 0.0288
-8.000 -0.7627 0.02538 0.01979 0.0037 0.4542 0.0280
-7.750 -0.7442 0.02353 0.01764 0.0050 0.4520 0.0285
-7.500 -0.7233 0.02205 0.01590 0.0060 0.4497 0.0287
-7.250 -0.7003 0.02101 0.01466 0.0069 0.4469 0.0289
-7.000 -0.6759 0.02028 0.01377 0.0076 0.4452 0.0291
-6.750 -0.6524 0.01902 0.01232 0.0084 0.4442 0.0293
-6.500 -0.6284 0.01770 0.01091 0.0091 0.4430 0.0297
-6.250 -0.6024 0.01709 0.01026 0.0096 0.4417 0.0299
-6.000 -0.5760 0.01661 0.00974 0.0100 0.4401 0.0302
-5.750 -0.5493 0.01618 0.00926 0.0104 0.4384 0.0305
-5.500 -0.5225 0.01574 0.00877 0.0109 0.4367 0.0308
-5.250 -0.4955 0.01532 0.00830 0.0113 0.4350 0.0312
-5.000 -0.4684 0.01493 0.00786 0.0117 0.4334 0.0316
-4.750 -0.4412 0.01460 0.00748 0.0121 0.4317 0.0321
-4.500 -0.4139 0.01427 0.00708 0.0124 0.4297 0.0325
-4.250 -0.3865 0.01399 0.00674 0.0128 0.4274 0.0328
-4.000 -0.3589 0.01375 0.00645 0.0132 0.4261 0.0330
-3.750 -0.3328 0.01298 0.00567 0.0137 0.4253 0.0335
-3.500 -0.3057 0.01259 0.00529 0.0141 0.4242 0.0340
-3.250 -0.2781 0.01231 0.00502 0.0144 0.4230 0.0345
-3.000 -0.2505 0.01207 0.00478 0.0147 0.4217 0.0350
-2.750 -0.2228 0.01184 0.00455 0.0150 0.4205 0.0356
-2.500 -0.1950 0.01163 0.00432 0.0154 0.4191 0.0362
-2.250 -0.1672 0.01144 0.00411 0.0157 0.4177 0.0368
-2.000 -0.1390 0.01130 0.00395 0.0159 0.4162 0.0372
-1.750 -0.1123 0.01092 0.00358 0.0164 0.4148 0.0384
-1.500 -0.0844 0.01077 0.00344 0.0166 0.4133 0.0393
-1.250 -0.0564 0.01066 0.00331 0.0169 0.4117 0.0402
-1.000 -0.0285 0.01060 0.00323 0.0171 0.4096 0.0412
-0.750 -0.0005 0.01052 0.00314 0.0174 0.4080 0.0421
-0.500 0.0273 0.01031 0.00296 0.0176 0.4072 0.0436
-0.250 0.0557 0.01018 0.00286 0.0178 0.4062 0.0452
0.000 0.0842 0.01009 0.00278 0.0180 0.4050 0.0468
0.250 0.1123 0.00995 0.00267 0.0182 0.4038 0.0495
0.500 0.1408 0.00987 0.00261 0.0184 0.4025 0.0523
0.750 0.1690 0.00976 0.00253 0.0186 0.4011 0.0568
1.000 0.1974 0.00965 0.00246 0.0187 0.3996 0.0647
1.250 0.2253 0.00950 0.00240 0.0189 0.3982 0.0885
1.500 0.2518 0.00915 0.00237 0.0193 0.3968 0.1849
1.750 0.2651 0.00749 0.00223 0.0215 0.3955 0.6678
2.000 0.2816 0.00700 0.00241 0.0245 0.3940 0.8790
2.250 0.3077 0.00715 0.00258 0.0253 0.3915 0.9014
2.500 0.3339 0.00723 0.00269 0.0261 0.3903 0.9171
2.750 0.3601 0.00727 0.00275 0.0270 0.3893 0.9291
3.000 0.3859 0.00733 0.00283 0.0279 0.3881 0.9389
3.250 0.4116 0.00737 0.00289 0.0289 0.3867 0.9481
3.500 0.4363 0.00743 0.00295 0.0300 0.3850 0.9580
3.750 0.4624 0.00754 0.00308 0.0311 0.3834 0.9698
4.000 0.4977 0.00760 0.00312 0.0299 0.3816 0.9723
4.250 0.5295 0.00763 0.00313 0.0292 0.3798 0.9732
4.500 0.5608 0.00768 0.00316 0.0286 0.3779 0.9741
4.750 0.5916 0.00782 0.00326 0.0281 0.3751 0.9750
5.000 0.6228 0.00786 0.00331 0.0275 0.3735 0.9760
5.250 0.6539 0.00787 0.00335 0.0270 0.3719 0.9771
5.500 0.6846 0.00790 0.00338 0.0265 0.3699 0.9783
5.750 0.7148 0.00792 0.00342 0.0261 0.3678 0.9796
6.000 0.7440 0.00795 0.00344 0.0259 0.3655 0.9813
6.250 0.7741 0.00798 0.00348 0.0256 0.3630 0.9826
6.500 0.8068 0.00809 0.00356 0.0246 0.3598 0.9831
6.750 0.8398 0.00815 0.00364 0.0236 0.3573 0.9837
7.000 0.8729 0.00812 0.00365 0.0225 0.3531 0.9843
7.250 0.9057 0.00811 0.00358 0.0215 0.3441 0.9849
7.500 0.9384 0.00812 0.00362 0.0206 0.3372 0.9857
7.750 0.9706 0.00821 0.00370 0.0196 0.3316 0.9866
8.000 1.0025 0.00832 0.00382 0.0188 0.3263 0.9876
8.250 1.0342 0.00842 0.00393 0.0179 0.3197 0.9887
8.500 1.0654 0.00858 0.00407 0.0171 0.3123 0.9901
8.750 1.0963 0.00874 0.00423 0.0163 0.3031 0.9916
9.000 1.1262 0.00895 0.00443 0.0157 0.2934 0.9932
9.250 1.1578 0.00922 0.00466 0.0147 0.2806 0.9942
9.500 1.1890 0.00959 0.00497 0.0136 0.2633 0.9954
9.750 1.2191 0.01014 0.00542 0.0124 0.2409 0.9969
10.000 1.2484 0.01087 0.00602 0.0113 0.2142 0.9985
10.250 1.2769 0.01178 0.00677 0.0100 0.1836 1.0000
10.500 1.2874 0.01265 0.00752 0.0122 0.1591 1.0000
10.750 1.2960 0.01362 0.00835 0.0147 0.1356 1.0000
11.000 1.3068 0.01472 0.00932 0.0164 0.1126 1.0000
11.250 1.3182 0.01589 0.01038 0.0178 0.0931 1.0000
11.500 1.3296 0.01704 0.01147 0.0190 0.0789 1.0000
11.750 1.3395 0.01828 0.01267 0.0201 0.0691 1.0000
12.000 1.3460 0.01973 0.01412 0.0211 0.0619 1.0000
12.250 1.3353 0.02303 0.01753 0.0206 0.0586 1.0000
12.500 1.3279 0.02695 0.02152 0.0189 0.0557 1.0000
12.750 1.3174 0.03086 0.02549 0.0179 0.0529 1.0000
13.000 1.3098 0.03428 0.02896 0.0173 0.0506 1.0000
13.250 1.2998 0.03788 0.03260 0.0167 0.0486 1.0000
13.500 1.2922 0.04121 0.03598 0.0161 0.0468 1.0000
13.750 1.2859 0.04441 0.03922 0.0156 0.0452 1.0000
14.000 1.2804 0.04749 0.04234 0.0152 0.0438 1.0000
14.250 1.2724 0.05096 0.04584 0.0145 0.0422 1.0000
14.500 1.2738 0.05351 0.04844 0.0141 0.0411 1.0000
14.750 1.2722 0.05650 0.05147 0.0135 0.0401 1.0000
15.000 1.2708 0.05946 0.05445 0.0129 0.0388 1.0000
15.250 1.2674 0.06273 0.05776 0.0121 0.0378 1.0000
15.500 1.2681 0.06554 0.06062 0.0116 0.0369 1.0000
15.750 1.2711 0.06804 0.06316 0.0111 0.0360 1.0000
16.000 1.2704 0.07109 0.06625 0.0104 0.0354 1.0000
16.250 1.2705 0.07403 0.06922 0.0097 0.0346 1.0000
16.500 1.2690 0.07717 0.07240 0.0090 0.0340 1.0000
16.750 1.2645 0.08073 0.07600 0.0081 0.0333 1.0000
17.000 1.2654 0.08364 0.07895 0.0074 0.0328 1.0000
17.250 1.2660 0.08662 0.08199 0.0067 0.0324 1.0000
17.500 1.2670 0.08953 0.08495 0.0060 0.0319 1.0000
17.750 1.2685 0.09240 0.08786 0.0052 0.0314 1.0000
18.000 1.2673 0.09570 0.09122 0.0043 0.0310 1.0000
18.250 1.2674 0.09882 0.09436 0.0034 0.0304 1.0000
18.500 1.2656 0.10220 0.09779 0.0023 0.0300 1.0000
18.750 1.2612 0.10600 0.10162 0.0011 0.0294 1.0000
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