ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 100,000 Max Cl/Cd: 49.47 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad10-il-100000-n5.txt Download as CSV file: xf-arad10-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 10% 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3776 0.09330 0.08815 -0.0259 1.0000 0.0374
-8.000 -0.3810 0.08992 0.08485 -0.0268 1.0000 0.0374
-7.750 -0.3838 0.08640 0.08140 -0.0283 1.0000 0.0375
-7.500 -0.3849 0.08260 0.07765 -0.0305 1.0000 0.0376
-7.250 -0.3858 0.07852 0.07363 -0.0327 1.0000 0.0376
-7.000 -0.3857 0.07392 0.06904 -0.0355 1.0000 0.0373
-6.750 -0.3849 0.06779 0.06287 -0.0396 1.0000 0.0367
-6.250 -0.3691 0.05059 0.04520 -0.0507 1.0000 0.0360
-6.000 -0.3542 0.04540 0.03976 -0.0528 1.0000 0.0365
-5.750 -0.3331 0.04052 0.03453 -0.0553 0.9991 0.0374
-5.500 -0.2949 0.03201 0.02485 -0.0618 0.9953 0.0409
-5.250 -0.2585 0.02956 0.02205 -0.0647 0.9908 0.0429
-5.000 -0.2213 0.02729 0.01936 -0.0674 0.9861 0.0454
-4.750 -0.1833 0.02547 0.01713 -0.0699 0.9817 0.0494
-4.500 -0.1467 0.02423 0.01563 -0.0719 0.9758 0.0539
-4.250 -0.1077 0.02331 0.01459 -0.0744 0.9713 0.0587
-4.000 -0.0713 0.02226 0.01328 -0.0762 0.9649 0.0648
-3.750 -0.0327 0.02162 0.01257 -0.0785 0.9593 0.0713
-3.500 0.0053 0.02097 0.01187 -0.0805 0.9536 0.0782
-3.250 0.0407 0.02030 0.01107 -0.0819 0.9455 0.0859
-3.000 0.0787 0.01977 0.01051 -0.0839 0.9395 0.0942
-2.750 0.1112 0.01929 0.01003 -0.0847 0.9293 0.1021
-2.500 0.1465 0.01879 0.00946 -0.0859 0.9213 0.1121
-2.250 0.1790 0.01840 0.00909 -0.0866 0.9109 0.1222
-2.000 0.2109 0.01802 0.00874 -0.0872 0.9003 0.1332
-1.750 0.2441 0.01763 0.00835 -0.0879 0.8909 0.1461
-1.500 0.2735 0.01736 0.00808 -0.0878 0.8780 0.1599
-1.250 0.3032 0.01709 0.00782 -0.0878 0.8655 0.1754
-0.750 0.3612 0.01651 0.00733 -0.0873 0.8376 0.2118
-0.500 0.3885 0.01622 0.00707 -0.0865 0.8180 0.2350
-0.250 0.4159 0.01593 0.00682 -0.0858 0.7971 0.2683
0.000 0.4433 0.01550 0.00662 -0.0853 0.7773 0.3425
0.500 0.4924 0.01377 0.00618 -0.0821 0.7402 1.0000
0.750 0.5199 0.01387 0.00609 -0.0815 0.7204 1.0000
1.000 0.5473 0.01399 0.00603 -0.0810 0.6997 1.0000
1.250 0.5746 0.01413 0.00599 -0.0804 0.6788 1.0000
1.500 0.6018 0.01429 0.00598 -0.0799 0.6576 1.0000
1.750 0.6289 0.01447 0.00599 -0.0794 0.6356 1.0000
2.000 0.6559 0.01466 0.00604 -0.0789 0.6118 1.0000
2.250 0.6827 0.01489 0.00609 -0.0784 0.5876 1.0000
2.500 0.7094 0.01513 0.00619 -0.0779 0.5607 1.0000
2.750 0.7357 0.01540 0.00630 -0.0774 0.5325 1.0000
3.000 0.7618 0.01572 0.00643 -0.0768 0.5022 1.0000
3.250 0.7875 0.01608 0.00660 -0.0763 0.4698 1.0000
3.500 0.8128 0.01648 0.00681 -0.0757 0.4360 1.0000
3.750 0.8379 0.01694 0.00706 -0.0752 0.4027 1.0000
4.000 0.8627 0.01744 0.00736 -0.0746 0.3714 1.0000
4.250 0.8874 0.01796 0.00770 -0.0741 0.3435 1.0000
4.500 0.9118 0.01852 0.00808 -0.0736 0.3210 1.0000
4.750 0.9365 0.01906 0.00851 -0.0731 0.3018 1.0000
5.000 0.9610 0.01962 0.00895 -0.0726 0.2857 1.0000
5.250 0.9852 0.02020 0.00942 -0.0721 0.2721 1.0000
5.500 1.0098 0.02074 0.00991 -0.0716 0.2598 1.0000
5.750 1.0342 0.02130 0.01044 -0.0711 0.2491 1.0000
6.000 1.0578 0.02193 0.01097 -0.0705 0.2399 1.0000
6.250 1.0824 0.02246 0.01154 -0.0701 0.2306 1.0000
6.500 1.1057 0.02310 0.01212 -0.0694 0.2230 1.0000
6.750 1.1298 0.02366 0.01273 -0.0689 0.2149 1.0000
7.000 1.1526 0.02435 0.01334 -0.0683 0.2085 1.0000
7.250 1.1764 0.02493 0.01402 -0.0677 0.2014 1.0000
7.500 1.1991 0.02559 0.01468 -0.0670 0.1952 1.0000
7.750 1.2218 0.02629 0.01539 -0.0664 0.1894 1.0000
8.000 1.2444 0.02695 0.01615 -0.0657 0.1835 1.0000
8.250 1.2659 0.02770 0.01686 -0.0649 0.1784 1.0000
8.500 1.2879 0.02843 0.01770 -0.0641 0.1731 1.0000
8.750 1.3091 0.02917 0.01853 -0.0633 0.1678 1.0000
9.000 1.3295 0.02997 0.01931 -0.0624 0.1635 1.0000
9.250 1.3500 0.03080 0.02027 -0.0615 0.1588 1.0000
9.500 1.3697 0.03162 0.02120 -0.0605 0.1540 1.0000
9.750 1.3883 0.03246 0.02208 -0.0594 0.1500 1.0000
10.000 1.4069 0.03341 0.02311 -0.0583 0.1461 1.0000
10.250 1.4243 0.03435 0.02424 -0.0570 0.1417 1.0000
10.500 1.4406 0.03527 0.02525 -0.0556 0.1379 1.0000
10.750 1.4563 0.03624 0.02622 -0.0542 0.1347 1.0000
11.000 1.4706 0.03737 0.02756 -0.0526 0.1311 1.0000
11.250 1.4832 0.03849 0.02886 -0.0508 0.1275 1.0000
11.500 1.4945 0.03956 0.03004 -0.0489 0.1243 1.0000
11.750 1.5040 0.04065 0.03115 -0.0468 0.1218 1.0000
12.000 1.5118 0.04204 0.03271 -0.0446 0.1191 1.0000
12.250 1.5173 0.04356 0.03447 -0.0423 0.1161 1.0000
12.500 1.5227 0.04508 0.03614 -0.0402 0.1133 1.0000
12.750 1.5284 0.04656 0.03772 -0.0383 0.1109 1.0000
13.000 1.5353 0.04805 0.03924 -0.0367 0.1089 1.0000
13.250 1.5364 0.05022 0.04164 -0.0349 0.1066 1.0000
13.500 1.5352 0.05262 0.04432 -0.0333 0.1042 1.0000
13.750 1.5342 0.05504 0.04693 -0.0319 0.1020 1.0000
14.000 1.5339 0.05741 0.04944 -0.0309 0.1000 1.0000
14.250 1.5353 0.05968 0.05179 -0.0301 0.0982 1.0000
14.500 1.5382 0.06194 0.05407 -0.0293 0.0965 1.0000
14.750 1.5247 0.06623 0.05871 -0.0291 0.0949 1.0000
15.000 1.5101 0.07088 0.06366 -0.0294 0.0933 1.0000
15.250 1.4945 0.07590 0.06894 -0.0303 0.0918 1.0000
15.500 1.4781 0.08125 0.07450 -0.0317 0.0904 1.0000
15.750 1.4616 0.08686 0.08030 -0.0335 0.0891 1.0000
16.000 1.4482 0.09226 0.08584 -0.0355 0.0879 1.0000
16.250 1.4451 0.09604 0.08967 -0.0367 0.0865 1.0000
16.500 1.4324 0.10166 0.09539 -0.0390 0.0854 1.0000
16.750 1.3524 0.12125 0.11541 -0.0509 0.0850 1.0000
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Polar data table (+)
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