ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 6% AIRFOIL (arad6-il) Reynolds number: 200,000 Max Cl/Cd: 93.01 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad6-il-200000.txt Download as CSV file: xf-arad6-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 6% 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3514 0.10046 0.09701 -0.0231 1.0000 0.0335
-7.500 -0.3605 0.09908 0.09569 -0.0205 1.0000 0.0342
-7.250 -0.3709 0.09781 0.09448 -0.0179 1.0000 0.0349
-7.000 -0.3763 0.09621 0.09294 -0.0173 1.0000 0.0361
-6.750 -0.3792 0.09513 0.09192 -0.0201 1.0000 0.0371
-6.500 -0.3723 0.09344 0.09025 -0.0259 1.0000 0.0376
-6.250 -0.3611 0.09069 0.08750 -0.0302 1.0000 0.0378
-6.000 -0.3594 0.08579 0.08264 -0.0302 1.0000 0.0382
-5.750 -0.3605 0.08245 0.07934 -0.0266 1.0000 0.0388
-5.500 -0.3474 0.07914 0.07604 -0.0265 0.9986 0.0398
-5.250 -0.3181 0.07517 0.07203 -0.0315 0.9955 0.0414
-5.000 -0.2824 0.07086 0.06766 -0.0391 0.9921 0.0438
-4.750 -0.1989 0.06513 0.06163 -0.0620 0.9879 0.0487
-4.500 -0.1699 0.05860 0.05507 -0.0674 0.9854 0.0499
-4.250 -0.1437 0.05546 0.05194 -0.0693 0.9833 0.0517
-4.000 -0.1110 0.05239 0.04881 -0.0734 0.9785 0.0553
-3.750 -0.0440 0.04622 0.04229 -0.0873 0.9758 0.0629
-3.500 -0.0112 0.04350 0.03955 -0.0903 0.9732 0.0654
-2.750 0.1572 0.02570 0.02012 -0.1134 0.9707 0.0465
-2.500 0.2003 0.02222 0.01599 -0.1169 0.9686 0.0454
-2.250 0.2392 0.02037 0.01361 -0.1190 0.9650 0.0472
-2.000 0.2802 0.01893 0.01177 -0.1214 0.9625 0.0486
-1.750 0.3218 0.01749 0.01020 -0.1243 0.9607 0.0541
-1.500 0.3636 0.01677 0.00945 -0.1271 0.9585 0.0691
-1.250 0.4067 0.01620 0.00889 -0.1302 0.9567 0.0982
-1.000 0.4370 0.01608 0.00882 -0.1308 0.9490 0.1230
-0.750 0.4779 0.01566 0.00842 -0.1335 0.9458 0.1485
-0.500 0.5211 0.01516 0.00800 -0.1367 0.9438 0.1776
-0.250 0.5569 0.01480 0.00778 -0.1384 0.9384 0.2091
0.000 0.5933 0.01440 0.00752 -0.1401 0.9330 0.2492
0.250 0.6333 0.01368 0.00724 -0.1427 0.9299 0.3515
0.500 0.6579 0.01221 0.00697 -0.1413 0.9214 1.0000
0.750 0.6965 0.01166 0.00628 -0.1425 0.9138 1.0000
1.000 0.7250 0.01132 0.00585 -0.1417 0.9006 1.0000
1.250 0.7523 0.01108 0.00555 -0.1407 0.8874 1.0000
1.500 0.7793 0.01093 0.00534 -0.1399 0.8746 1.0000
1.750 0.8064 0.01085 0.00523 -0.1392 0.8624 1.0000
2.000 0.8335 0.01079 0.00513 -0.1385 0.8500 1.0000
2.250 0.8604 0.01074 0.00505 -0.1377 0.8362 1.0000
2.500 0.8871 0.01072 0.00499 -0.1370 0.8210 1.0000
2.750 0.9136 0.01072 0.00498 -0.1362 0.8043 1.0000
3.000 0.9402 0.01074 0.00495 -0.1354 0.7863 1.0000
3.250 0.9663 0.01080 0.00497 -0.1346 0.7652 1.0000
3.500 0.9923 0.01089 0.00499 -0.1337 0.7419 1.0000
3.750 1.0177 0.01102 0.00508 -0.1328 0.7144 1.0000
4.000 1.0426 0.01121 0.00517 -0.1318 0.6820 1.0000
4.250 1.0668 0.01148 0.00530 -0.1307 0.6414 1.0000
4.500 1.0897 0.01187 0.00549 -0.1294 0.5883 1.0000
4.750 1.1099 0.01252 0.00579 -0.1276 0.5117 1.0000
5.000 1.1263 0.01360 0.00627 -0.1255 0.4068 1.0000
5.250 1.1428 0.01481 0.00694 -0.1236 0.3207 1.0000
5.500 1.1621 0.01580 0.00762 -0.1222 0.2753 1.0000
5.750 1.1829 0.01664 0.00827 -0.1211 0.2467 1.0000
6.000 1.2048 0.01734 0.00893 -0.1202 0.2240 1.0000
6.250 1.2262 0.01809 0.00957 -0.1191 0.2057 1.0000
6.500 1.2473 0.01885 0.01026 -0.1181 0.1896 1.0000
6.750 1.2690 0.01953 0.01092 -0.1171 0.1743 1.0000
7.000 1.2901 0.02025 0.01164 -0.1160 0.1602 1.0000
7.250 1.3108 0.02099 0.01236 -0.1149 0.1468 1.0000
7.500 1.3316 0.02169 0.01308 -0.1137 0.1343 1.0000
7.750 1.3523 0.02239 0.01386 -0.1125 0.1229 1.0000
8.000 1.3719 0.02321 0.01474 -0.1112 0.1121 1.0000
8.250 1.3905 0.02414 0.01568 -0.1097 0.1024 1.0000
8.500 1.4079 0.02522 0.01672 -0.1081 0.0939 1.0000
8.750 1.4270 0.02604 0.01770 -0.1066 0.0862 1.0000
9.000 1.4432 0.02724 0.01890 -0.1049 0.0790 1.0000
9.250 1.4602 0.02787 0.01965 -0.1032 0.0717 1.0000
9.500 1.4751 0.02889 0.02078 -0.1013 0.0647 1.0000
9.750 1.4887 0.02977 0.02170 -0.0992 0.0585 1.0000
10.000 1.5017 0.03096 0.02304 -0.0970 0.0529 1.0000
10.250 1.5108 0.03201 0.02413 -0.0943 0.0472 1.0000
10.500 1.5193 0.03335 0.02565 -0.0913 0.0416 1.0000
10.750 1.5226 0.03513 0.02743 -0.0880 0.0367 1.0000
11.000 1.5289 0.03695 0.02949 -0.0849 0.0323 1.0000
11.250 1.5330 0.03865 0.03129 -0.0820 0.0292 1.0000
11.500 1.5338 0.04145 0.03422 -0.0788 0.0268 1.0000
11.750 1.5381 0.04331 0.03633 -0.0762 0.0248 1.0000
12.000 1.5408 0.04532 0.03849 -0.0737 0.0232 1.0000
12.250 1.5416 0.04765 0.04093 -0.0713 0.0221 1.0000
12.500 1.5395 0.05075 0.04416 -0.0688 0.0212 1.0000
12.750 1.5319 0.05512 0.04879 -0.0661 0.0205 1.0000
13.000 1.5264 0.05834 0.05230 -0.0640 0.0202 1.0000
13.250 1.5182 0.06205 0.05630 -0.0622 0.0199 1.0000
13.500 1.5073 0.06622 0.06077 -0.0608 0.0196 1.0000
13.750 1.4938 0.07089 0.06572 -0.0600 0.0194 1.0000
14.000 1.4780 0.07607 0.07117 -0.0598 0.0193 1.0000
14.250 1.4602 0.08182 0.07719 -0.0605 0.0192 1.0000
14.500 1.4408 0.08819 0.08381 -0.0621 0.0192 1.0000
14.750 1.4201 0.09524 0.09111 -0.0647 0.0193 1.0000
15.000 1.3985 0.10313 0.09923 -0.0685 0.0194 1.0000
15.250 1.3762 0.11188 0.10820 -0.0734 0.0195 1.0000
15.500 1.3534 0.12150 0.11802 -0.0794 0.0197 1.0000
15.750 1.3296 0.13224 0.12894 -0.0865 0.0199 1.0000
16.000 1.3049 0.14408 0.14093 -0.0945 0.0202 1.0000
16.250 0.8998 0.17495 0.17206 -0.0901 0.0351 1.0000
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Polar data table (+)
Polar graphs
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