ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: ARA-D 20% AIRFOIL (arad20-il) Reynolds number: 200,000 Max Cl/Cd: 51.96 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad20-il-200000.txt Download as CSV file: xf-arad20-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7903 0.09603 0.09157 -0.0240 1.0000 0.0436
-14.750 -0.8303 0.08514 0.08047 -0.0315 1.0000 0.0434
-14.500 -0.8680 0.07568 0.07076 -0.0378 1.0000 0.0431
-14.250 -0.9022 0.06782 0.06262 -0.0425 1.0000 0.0430
-14.000 -0.9319 0.06145 0.05597 -0.0454 1.0000 0.0430
-13.750 -0.9577 0.05633 0.05055 -0.0464 1.0000 0.0431
-13.500 -0.9807 0.05221 0.04612 -0.0457 1.0000 0.0432
-13.250 -1.0022 0.04898 0.04260 -0.0431 1.0000 0.0434
-13.000 -1.0182 0.04625 0.03951 -0.0399 1.0000 0.0436
-12.750 -1.0045 0.04419 0.03746 -0.0390 1.0000 0.0442
-12.500 -0.9906 0.04262 0.03589 -0.0380 1.0000 0.0448
-12.250 -0.9764 0.04111 0.03434 -0.0369 1.0000 0.0455
-12.000 -0.9645 0.03936 0.03244 -0.0357 1.0000 0.0464
-11.750 -0.9532 0.03743 0.03026 -0.0343 1.0000 0.0474
-11.500 -0.9420 0.03551 0.02796 -0.0327 1.0000 0.0484
-11.250 -0.9184 0.03418 0.02677 -0.0325 1.0000 0.0495
-11.000 -0.8967 0.03314 0.02573 -0.0319 1.0000 0.0508
-10.750 -0.8768 0.03190 0.02432 -0.0311 1.0000 0.0526
-10.500 -0.8547 0.03060 0.02297 -0.0306 1.0000 0.0543
-10.250 -0.8308 0.02970 0.02213 -0.0303 1.0000 0.0560
-10.000 -0.8076 0.02865 0.02094 -0.0298 1.0000 0.0582
-9.750 -0.7829 0.02753 0.01990 -0.0295 1.0000 0.0601
-9.500 -0.7577 0.02668 0.01910 -0.0293 1.0000 0.0624
-9.250 -0.7208 0.02566 0.01801 -0.0314 0.9324 0.0656
-9.000 -0.6983 0.02535 0.01743 -0.0296 0.8030 0.0683
-8.750 -0.6775 0.02493 0.01656 -0.0278 0.7335 0.0714
-8.500 -0.6532 0.02447 0.01598 -0.0271 0.6956 0.0745
-8.250 -0.6274 0.02394 0.01521 -0.0267 0.6707 0.0784
-8.000 -0.6012 0.02347 0.01468 -0.0264 0.6521 0.0822
-7.750 -0.5744 0.02291 0.01401 -0.0262 0.6366 0.0866
-7.500 -0.5470 0.02250 0.01351 -0.0261 0.6242 0.0917
-7.250 -0.5198 0.02194 0.01295 -0.0260 0.6131 0.0967
-7.000 -0.4921 0.02149 0.01241 -0.0259 0.6034 0.1030
-6.750 -0.4638 0.02106 0.01197 -0.0260 0.5938 0.1101
-6.500 -0.4361 0.02061 0.01151 -0.0260 0.5857 0.1181
-6.250 -0.4076 0.02014 0.01108 -0.0262 0.5781 0.1279
-6.000 -0.3789 0.01969 0.01067 -0.0263 0.5703 0.1399
-5.750 -0.3503 0.01932 0.01029 -0.0265 0.5633 0.1546
-5.500 -0.3211 0.01897 0.00999 -0.0267 0.5569 0.1727
-5.250 -0.2919 0.01851 0.00969 -0.0271 0.5502 0.1944
-5.000 -0.2625 0.01817 0.00941 -0.0274 0.5437 0.2214
-4.750 -0.2334 0.01793 0.00925 -0.0277 0.5377 0.2532
-4.500 -0.2034 0.01757 0.00909 -0.0282 0.5320 0.2898
-4.250 -0.1735 0.01728 0.00897 -0.0286 0.5258 0.3297
-4.000 -0.1437 0.01707 0.00887 -0.0290 0.5200 0.3710
-3.750 -0.1140 0.01705 0.00890 -0.0292 0.5145 0.4124
-3.500 -0.0837 0.01685 0.00890 -0.0296 0.5092 0.4533
-3.250 -0.0535 0.01673 0.00891 -0.0299 0.5033 0.4923
-3.000 -0.0235 0.01668 0.00892 -0.0300 0.4978 0.5292
-2.750 0.0061 0.01677 0.00903 -0.0301 0.4928 0.5621
-2.500 0.0363 0.01677 0.00914 -0.0303 0.4876 0.5937
-2.250 0.0665 0.01676 0.00920 -0.0304 0.4818 0.6232
-2.000 0.0960 0.01677 0.00926 -0.0303 0.4765 0.6500
-1.750 0.1252 0.01688 0.00935 -0.0302 0.4719 0.6758
-1.500 0.1544 0.01701 0.00954 -0.0300 0.4668 0.7006
-1.250 0.1835 0.01704 0.00965 -0.0299 0.4612 0.7242
-1.000 0.2123 0.01709 0.00972 -0.0296 0.4559 0.7462
-0.750 0.2407 0.01719 0.00977 -0.0292 0.4515 0.7674
-0.500 0.2689 0.01740 0.00996 -0.0288 0.4467 0.7879
-0.250 0.2971 0.01744 0.01007 -0.0285 0.4412 0.8079
0.000 0.3239 0.01748 0.01013 -0.0277 0.4360 0.8264
0.250 0.3499 0.01753 0.01014 -0.0267 0.4317 0.8442
0.500 0.3753 0.01774 0.01026 -0.0257 0.4274 0.8620
0.750 0.4003 0.01772 0.01035 -0.0246 0.4221 0.8800
1.000 0.4246 0.01770 0.01034 -0.0233 0.4170 0.8985
1.250 0.4483 0.01765 0.01024 -0.0219 0.4127 0.9175
1.500 0.4726 0.01765 0.01014 -0.0206 0.4087 0.9372
1.750 0.5016 0.01765 0.01018 -0.0205 0.4035 0.9567
2.000 0.5385 0.01764 0.01017 -0.0222 0.3977 0.9731
2.250 0.5812 0.01769 0.01012 -0.0252 0.3925 0.9854
2.500 0.6254 0.01795 0.01022 -0.0286 0.3877 0.9954
2.750 0.6565 0.01801 0.01035 -0.0299 0.3822 1.0000
3.000 0.6810 0.01808 0.01037 -0.0298 0.3773 1.0000
3.250 0.7106 0.01820 0.01037 -0.0305 0.3730 1.0000
3.500 0.7411 0.01853 0.01056 -0.0314 0.3688 1.0000
3.750 0.7714 0.01874 0.01085 -0.0322 0.3634 1.0000
4.000 0.8020 0.01892 0.01097 -0.0330 0.3584 1.0000
4.250 0.8328 0.01910 0.01104 -0.0338 0.3542 1.0000
4.500 0.8631 0.01947 0.01133 -0.0345 0.3500 1.0000
4.750 0.8926 0.01974 0.01167 -0.0351 0.3449 1.0000
5.000 0.9226 0.01995 0.01185 -0.0357 0.3402 1.0000
5.250 0.9526 0.02018 0.01196 -0.0363 0.3362 1.0000
5.500 0.9819 0.02061 0.01234 -0.0369 0.3320 1.0000
5.750 1.0105 0.02094 0.01275 -0.0373 0.3272 1.0000
6.000 1.0396 0.02120 0.01298 -0.0378 0.3228 1.0000
6.250 1.0689 0.02147 0.01315 -0.0383 0.3190 1.0000
6.500 1.0973 0.02196 0.01362 -0.0387 0.3149 1.0000
6.750 1.1245 0.02236 0.01411 -0.0390 0.3105 1.0000
7.000 1.1526 0.02269 0.01443 -0.0393 0.3064 1.0000
7.250 1.1811 0.02300 0.01466 -0.0397 0.3027 1.0000
7.500 1.2089 0.02355 0.01514 -0.0401 0.2990 1.0000
7.750 1.2343 0.02403 0.01576 -0.0402 0.2949 1.0000
8.000 1.2607 0.02444 0.01621 -0.0403 0.2910 1.0000
8.250 1.2881 0.02479 0.01650 -0.0406 0.2874 1.0000
8.500 1.3164 0.02535 0.01691 -0.0410 0.2840 1.0000
8.750 1.3391 0.02595 0.01769 -0.0407 0.2804 1.0000
9.000 1.3630 0.02649 0.01832 -0.0406 0.2766 1.0000
9.250 1.3882 0.02693 0.01876 -0.0406 0.2732 1.0000
9.500 1.4147 0.02736 0.01911 -0.0407 0.2701 1.0000
9.750 1.4392 0.02810 0.01984 -0.0408 0.2668 1.0000
10.000 1.4582 0.02883 0.02075 -0.0400 0.2634 1.0000
10.250 1.4793 0.02945 0.02144 -0.0396 0.2600 1.0000
10.500 1.5025 0.02994 0.02192 -0.0393 0.2569 1.0000
10.750 1.5281 0.03047 0.02235 -0.0394 0.2541 1.0000
11.000 1.5472 0.03140 0.02335 -0.0388 0.2511 1.0000
11.250 1.5595 0.03235 0.02448 -0.0373 0.2481 1.0000
11.500 1.5745 0.03315 0.02537 -0.0361 0.2450 1.0000
11.750 1.5929 0.03378 0.02600 -0.0354 0.2422 1.0000
12.000 1.6162 0.03433 0.02649 -0.0352 0.2396 1.0000
12.250 1.6335 0.03538 0.02755 -0.0345 0.2370 1.0000
12.500 1.6291 0.03682 0.02922 -0.0311 0.2345 1.0000
12.750 1.6239 0.03834 0.03089 -0.0277 0.2320 1.0000
13.000 1.6273 0.03969 0.03233 -0.0258 0.2295 1.0000
13.250 1.6405 0.04065 0.03328 -0.0249 0.2270 1.0000
13.500 1.6664 0.04113 0.03366 -0.0251 0.2246 1.0000
13.750 1.6643 0.04325 0.03590 -0.0234 0.2223 1.0000
14.000 1.6400 0.04694 0.03988 -0.0215 0.2201 1.0000
14.250 1.6232 0.05067 0.04380 -0.0209 0.2175 1.0000
14.500 1.6203 0.05343 0.04665 -0.0209 0.2150 1.0000
14.750 1.6356 0.05449 0.04769 -0.0208 0.2127 1.0000
15.000 1.6712 0.05379 0.04683 -0.0205 0.2105 1.0000
15.250 1.6377 0.05976 0.05307 -0.0210 0.2082 1.0000
15.500 1.3077 0.10685 0.10125 -0.0367 0.1977 1.0000
15.750 1.3950 0.09691 0.09118 -0.0328 0.1987 1.0000
16.000 1.4902 0.08654 0.08060 -0.0287 0.1988 1.0000
16.250 1.5593 0.08040 0.07427 -0.0261 0.1978 1.0000
16.500 0.9209 0.20433 0.19931 -0.0841 0.1578 1.0000
16.750 0.9311 0.20769 0.20270 -0.0856 0.1588 1.0000
|
Polar data table (+)
Polar graphs
<< Back to ARA-D 20% AIRFOIL (arad20-il)