ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 20% AIRFOIL (arad20-il) Reynolds number: 100,000 Max Cl/Cd: 38.59 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad20-il-100000-n5.txt Download as CSV file: xf-arad20-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 20% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7445 0.09157 0.08544 -0.0245 1.0000 0.0431
-14.000 -0.8050 0.07723 0.07066 -0.0347 1.0000 0.0429
-13.750 -0.8391 0.06871 0.06181 -0.0400 1.0000 0.0430
-13.500 -0.8638 0.06234 0.05511 -0.0432 1.0000 0.0433
-13.250 -0.8836 0.05716 0.04960 -0.0448 1.0000 0.0437
-13.000 -0.8825 0.05457 0.04698 -0.0449 1.0000 0.0441
-12.750 -0.8823 0.05207 0.04441 -0.0446 1.0000 0.0446
-12.500 -0.8829 0.04969 0.04193 -0.0439 1.0000 0.0452
-12.250 -0.8848 0.04744 0.03957 -0.0426 1.0000 0.0460
-12.000 -0.8876 0.04533 0.03729 -0.0405 1.0000 0.0469
-11.750 -0.8865 0.04309 0.03475 -0.0387 1.0000 0.0482
-11.500 -0.8746 0.04171 0.03339 -0.0375 1.0000 0.0492
-11.250 -0.8614 0.04039 0.03205 -0.0365 1.0000 0.0504
-11.000 -0.8478 0.03887 0.03040 -0.0354 1.0000 0.0520
-10.750 -0.8326 0.03728 0.02864 -0.0344 1.0000 0.0537
-10.500 -0.8142 0.03620 0.02761 -0.0336 1.0000 0.0551
-10.250 -0.7954 0.03501 0.02636 -0.0329 1.0000 0.0571
-10.000 -0.7758 0.03377 0.02503 -0.0322 1.0000 0.0593
-9.750 -0.7548 0.03280 0.02413 -0.0317 1.0000 0.0613
-9.500 -0.7271 0.03169 0.02286 -0.0324 0.9461 0.0644
-9.250 -0.6966 0.03086 0.02196 -0.0332 0.8509 0.0672
-9.000 -0.6760 0.03020 0.02095 -0.0316 0.7791 0.0703
-8.750 -0.6557 0.02961 0.02016 -0.0302 0.7299 0.0730
-8.500 -0.6331 0.02900 0.01928 -0.0292 0.6957 0.0768
-8.250 -0.6097 0.02837 0.01854 -0.0286 0.6705 0.0802
-8.000 -0.5849 0.02777 0.01772 -0.0281 0.6508 0.0848
-7.750 -0.5601 0.02717 0.01708 -0.0277 0.6343 0.0891
-7.500 -0.5343 0.02658 0.01638 -0.0274 0.6205 0.0943
-7.250 -0.5084 0.02606 0.01574 -0.0271 0.6089 0.1004
-7.000 -0.4820 0.02549 0.01517 -0.0270 0.5983 0.1067
-6.750 -0.4555 0.02498 0.01460 -0.0269 0.5886 0.1142
-6.500 -0.4285 0.02452 0.01407 -0.0267 0.5801 0.1230
-6.250 -0.4009 0.02405 0.01359 -0.0268 0.5713 0.1334
-6.000 -0.3734 0.02364 0.01314 -0.0267 0.5639 0.1452
-5.750 -0.3456 0.02323 0.01273 -0.0268 0.5568 0.1591
-5.500 -0.3173 0.02281 0.01237 -0.0270 0.5493 0.1753
-5.250 -0.2891 0.02244 0.01203 -0.0271 0.5426 0.1948
-5.000 -0.2608 0.02216 0.01173 -0.0272 0.5368 0.2181
-4.750 -0.2319 0.02179 0.01151 -0.0275 0.5301 0.2448
-4.250 -0.1744 0.02123 0.01111 -0.0279 0.5179 0.3101
-4.000 -0.1456 0.02102 0.01098 -0.0281 0.5127 0.3462
-3.750 -0.1162 0.02081 0.01092 -0.0284 0.5065 0.3836
-3.250 -0.0582 0.02054 0.01082 -0.0285 0.4953 0.4580
-3.000 -0.0293 0.02050 0.01082 -0.0285 0.4905 0.4933
-2.750 0.0001 0.02044 0.01089 -0.0285 0.4845 0.5279
-2.500 0.0291 0.02042 0.01094 -0.0284 0.4788 0.5602
-2.250 0.0577 0.02043 0.01097 -0.0282 0.4738 0.5915
-2.000 0.0865 0.02051 0.01100 -0.0280 0.4694 0.6212
-1.750 0.1152 0.02055 0.01116 -0.0278 0.4636 0.6482
-1.500 0.1434 0.02061 0.01126 -0.0274 0.4580 0.6737
-1.250 0.1713 0.02068 0.01131 -0.0270 0.4531 0.6981
-1.000 0.1990 0.02078 0.01135 -0.0264 0.4490 0.7212
-0.750 0.2269 0.02089 0.01152 -0.0261 0.4435 0.7433
-0.500 0.2545 0.02100 0.01164 -0.0256 0.4379 0.7647
-0.250 0.2819 0.02109 0.01169 -0.0251 0.4330 0.7856
0.000 0.3088 0.02117 0.01170 -0.0244 0.4290 0.8055
0.250 0.3351 0.02129 0.01185 -0.0237 0.4240 0.8242
0.500 0.3614 0.02140 0.01199 -0.0230 0.4184 0.8430
0.750 0.3877 0.02146 0.01202 -0.0222 0.4136 0.8618
1.000 0.4142 0.02150 0.01198 -0.0215 0.4095 0.8808
1.250 0.4413 0.02160 0.01206 -0.0211 0.4049 0.9000
1.500 0.4698 0.02172 0.01221 -0.0210 0.3992 0.9193
1.750 0.5010 0.02179 0.01223 -0.0215 0.3941 0.9384
2.000 0.5358 0.02185 0.01218 -0.0228 0.3899 0.9566
2.250 0.5735 0.02205 0.01237 -0.0249 0.3845 0.9741
2.750 0.6424 0.02237 0.01260 -0.0283 0.3739 1.0000
3.000 0.6698 0.02252 0.01261 -0.0286 0.3703 1.0000
3.250 0.6975 0.02288 0.01298 -0.0291 0.3650 1.0000
3.500 0.7258 0.02320 0.01328 -0.0296 0.3598 1.0000
3.750 0.7546 0.02344 0.01344 -0.0301 0.3555 1.0000
4.000 0.7837 0.02366 0.01352 -0.0305 0.3519 1.0000
4.250 0.8115 0.02413 0.01404 -0.0310 0.3466 1.0000
4.500 0.8396 0.02451 0.01442 -0.0315 0.3416 1.0000
4.750 0.8680 0.02479 0.01463 -0.0319 0.3375 1.0000
5.000 0.8967 0.02505 0.01476 -0.0322 0.3341 1.0000
5.250 0.9233 0.02562 0.01543 -0.0326 0.3290 1.0000
5.500 0.9503 0.02607 0.01589 -0.0328 0.3243 1.0000
5.750 0.9778 0.02641 0.01618 -0.0331 0.3203 1.0000
6.000 1.0057 0.02672 0.01637 -0.0334 0.3171 1.0000
6.250 1.0306 0.02739 0.01715 -0.0335 0.3124 1.0000
6.500 1.0559 0.02795 0.01775 -0.0336 0.3078 1.0000
6.750 1.0820 0.02837 0.01815 -0.0337 0.3040 1.0000
7.000 1.1088 0.02873 0.01841 -0.0338 0.3009 1.0000
7.250 1.1320 0.02946 0.01923 -0.0337 0.2968 1.0000
7.500 1.1545 0.03020 0.02006 -0.0336 0.2925 1.0000
7.750 1.1782 0.03076 0.02062 -0.0334 0.2888 1.0000
8.000 1.2030 0.03120 0.02100 -0.0333 0.2856 1.0000
8.250 1.2259 0.03184 0.02165 -0.0331 0.2824 1.0000
8.500 1.2432 0.03288 0.02284 -0.0325 0.2783 1.0000
8.750 1.2623 0.03370 0.02373 -0.0319 0.2746 1.0000
9.000 1.2832 0.03432 0.02435 -0.0314 0.2715 1.0000
9.250 1.3064 0.03482 0.02477 -0.0312 0.2688 1.0000
9.500 1.3191 0.03601 0.02609 -0.0300 0.2654 1.0000
9.750 1.3272 0.03738 0.02763 -0.0284 0.2619 1.0000
10.000 1.3374 0.03853 0.02886 -0.0270 0.2587 1.0000
10.250 1.3511 0.03942 0.02975 -0.0258 0.2559 1.0000
10.500 1.3686 0.04005 0.03033 -0.0249 0.2535 1.0000
10.750 1.3636 0.04203 0.03246 -0.0223 0.2508 1.0000
11.000 1.3445 0.04541 0.03609 -0.0201 0.2476 1.0000
11.250 1.3323 0.04882 0.03966 -0.0193 0.2443 1.0000
11.500 1.3342 0.05118 0.04207 -0.0191 0.2415 1.0000
11.750 1.3525 0.05196 0.04280 -0.0189 0.2392 1.0000
12.000 1.3324 0.05692 0.04794 -0.0195 0.2361 1.0000
12.250 1.1083 0.09051 0.08225 -0.0302 0.2220 1.0000
12.500 1.1602 0.08615 0.07782 -0.0284 0.2226 1.0000
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