ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 10% AIRFOIL (arad10-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.58 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad10-il-1000000.txt Download as CSV file: xf-arad10-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7746 0.04125 0.03882 -0.0658 1.0000 0.0133
-10.750 -0.7708 0.03023 0.02715 -0.0728 1.0000 0.0133
-10.500 -0.7561 0.02585 0.02234 -0.0743 1.0000 0.0134
-10.250 -0.7355 0.02333 0.01957 -0.0749 1.0000 0.0136
-10.000 -0.7123 0.02167 0.01774 -0.0751 1.0000 0.0138
-9.750 -0.6882 0.02045 0.01639 -0.0751 1.0000 0.0139
-9.500 -0.6646 0.01944 0.01528 -0.0748 1.0000 0.0141
-9.250 -0.6423 0.01858 0.01433 -0.0741 1.0000 0.0143
-9.000 -0.6221 0.01784 0.01350 -0.0729 1.0000 0.0145
-8.750 -0.5936 0.01703 0.01258 -0.0733 0.9991 0.0147
-8.500 -0.5606 0.01620 0.01165 -0.0747 0.9977 0.0150
-8.250 -0.5272 0.01544 0.01078 -0.0760 0.9963 0.0153
-8.000 -0.4933 0.01479 0.01004 -0.0774 0.9950 0.0157
-7.750 -0.4589 0.01429 0.00945 -0.0788 0.9940 0.0160
-7.500 -0.4262 0.01338 0.00843 -0.0801 0.9916 0.0164
-7.250 -0.3935 0.01272 0.00771 -0.0812 0.9883 0.0169
-7.000 -0.3602 0.01227 0.00722 -0.0823 0.9849 0.0174
-6.750 -0.3285 0.01187 0.00678 -0.0830 0.9799 0.0179
-6.500 -0.2985 0.01152 0.00638 -0.0833 0.9733 0.0185
-6.250 -0.2699 0.01123 0.00603 -0.0832 0.9658 0.0190
-6.000 -0.2426 0.01080 0.00555 -0.0828 0.9575 0.0198
-5.750 -0.2152 0.01050 0.00522 -0.0824 0.9487 0.0208
-5.500 -0.1882 0.01028 0.00496 -0.0819 0.9401 0.0219
-5.250 -0.1602 0.00998 0.00462 -0.0817 0.9305 0.0234
-5.000 -0.1325 0.00976 0.00437 -0.0814 0.9214 0.0255
-4.750 -0.1043 0.00952 0.00412 -0.0812 0.9112 0.0284
-4.500 -0.0758 0.00933 0.00392 -0.0810 0.9010 0.0321
-4.250 -0.0476 0.00922 0.00376 -0.0808 0.8904 0.0356
-4.000 -0.0188 0.00903 0.00358 -0.0807 0.8787 0.0398
-3.750 0.0100 0.00889 0.00341 -0.0807 0.8671 0.0436
-3.500 0.0387 0.00880 0.00328 -0.0806 0.8547 0.0472
-3.250 0.0675 0.00868 0.00312 -0.0805 0.8394 0.0514
-3.000 0.0961 0.00864 0.00300 -0.0804 0.8191 0.0552
-2.750 0.1248 0.00855 0.00286 -0.0803 0.7965 0.0608
-2.500 0.1537 0.00851 0.00275 -0.0803 0.7762 0.0661
-2.250 0.1827 0.00848 0.00267 -0.0803 0.7572 0.0730
-2.000 0.2118 0.00843 0.00259 -0.0804 0.7385 0.0819
-1.750 0.2411 0.00839 0.00252 -0.0805 0.7213 0.0909
-1.250 0.2996 0.00836 0.00242 -0.0807 0.6880 0.1094
-1.000 0.3288 0.00835 0.00239 -0.0809 0.6707 0.1204
-0.750 0.3581 0.00836 0.00236 -0.0810 0.6544 0.1300
-0.500 0.3873 0.00838 0.00235 -0.0811 0.6375 0.1408
-0.250 0.4166 0.00839 0.00234 -0.0813 0.6190 0.1532
0.000 0.4458 0.00842 0.00233 -0.0814 0.6001 0.1659
0.250 0.4750 0.00845 0.00234 -0.0816 0.5819 0.1816
0.500 0.5041 0.00848 0.00236 -0.0818 0.5613 0.2022
0.750 0.5330 0.00852 0.00239 -0.0819 0.5382 0.2356
1.000 0.5621 0.00845 0.00244 -0.0822 0.5159 0.3097
1.250 0.5825 0.00673 0.00241 -0.0808 0.4944 1.0000
1.500 0.6113 0.00694 0.00247 -0.0809 0.4669 1.0000
1.750 0.6398 0.00719 0.00255 -0.0810 0.4359 1.0000
2.000 0.6683 0.00745 0.00264 -0.0811 0.4044 1.0000
2.250 0.6966 0.00775 0.00275 -0.0812 0.3701 1.0000
2.500 0.7247 0.00807 0.00289 -0.0813 0.3337 1.0000
2.750 0.7528 0.00839 0.00303 -0.0813 0.3033 1.0000
3.000 0.7811 0.00866 0.00317 -0.0814 0.2797 1.0000
3.250 0.8093 0.00893 0.00332 -0.0815 0.2600 1.0000
3.500 0.8376 0.00917 0.00346 -0.0816 0.2447 1.0000
3.750 0.8659 0.00939 0.00361 -0.0817 0.2318 1.0000
4.000 0.8941 0.00961 0.00376 -0.0818 0.2198 1.0000
4.250 0.9222 0.00986 0.00392 -0.0818 0.2088 1.0000
4.500 0.9505 0.01004 0.00407 -0.0819 0.2011 1.0000
4.750 0.9785 0.01028 0.00425 -0.0820 0.1923 1.0000
5.000 1.0066 0.01046 0.00440 -0.0820 0.1859 1.0000
5.250 1.0343 0.01072 0.00459 -0.0820 0.1779 1.0000
5.500 1.0624 0.01089 0.00476 -0.0821 0.1735 1.0000
5.750 1.0901 0.01111 0.00495 -0.0821 0.1678 1.0000
6.000 1.1175 0.01136 0.00516 -0.0821 0.1617 1.0000
6.250 1.1453 0.01154 0.00535 -0.0821 0.1576 1.0000
6.500 1.1726 0.01179 0.00556 -0.0821 0.1525 1.0000
6.750 1.1996 0.01205 0.00580 -0.0820 0.1473 1.0000
7.000 1.2271 0.01224 0.00600 -0.0820 0.1436 1.0000
7.250 1.2540 0.01250 0.00623 -0.0819 0.1391 1.0000
7.500 1.2804 0.01281 0.00651 -0.0818 0.1338 1.0000
7.750 1.3075 0.01300 0.00672 -0.0817 0.1306 1.0000
8.000 1.3339 0.01327 0.00697 -0.0816 0.1266 1.0000
8.250 1.3595 0.01363 0.00730 -0.0813 0.1212 1.0000
8.500 1.3861 0.01384 0.00755 -0.0812 0.1185 1.0000
8.750 1.4120 0.01412 0.00782 -0.0810 0.1148 1.0000
9.000 1.4371 0.01449 0.00816 -0.0806 0.1102 1.0000
9.250 1.4625 0.01479 0.00848 -0.0804 0.1070 1.0000
9.500 1.4878 0.01507 0.00878 -0.0801 0.1038 1.0000
9.750 1.5122 0.01545 0.00913 -0.0796 0.0999 1.0000
10.000 1.5361 0.01586 0.00955 -0.0791 0.0961 1.0000
10.250 1.5608 0.01615 0.00987 -0.0787 0.0937 1.0000
10.500 1.5844 0.01652 0.01025 -0.0782 0.0906 1.0000
10.750 1.6067 0.01700 0.01071 -0.0775 0.0870 1.0000
11.000 1.6296 0.01739 0.01114 -0.0768 0.0847 1.0000
11.250 1.6525 0.01775 0.01154 -0.0762 0.0825 1.0000
11.500 1.6740 0.01819 0.01199 -0.0753 0.0798 1.0000
11.750 1.6936 0.01877 0.01256 -0.0742 0.0764 1.0000
12.000 1.7143 0.01920 0.01304 -0.0732 0.0746 1.0000
12.250 1.7348 0.01962 0.01351 -0.0722 0.0725 1.0000
12.500 1.7533 0.02015 0.01405 -0.0709 0.0698 1.0000
12.750 1.7687 0.02086 0.01476 -0.0691 0.0667 1.0000
13.000 1.7865 0.02135 0.01531 -0.0677 0.0652 1.0000
13.250 1.8026 0.02189 0.01590 -0.0661 0.0633 1.0000
13.500 1.8133 0.02259 0.01662 -0.0635 0.0613 1.0000
13.750 1.8216 0.02348 0.01754 -0.0607 0.0589 1.0000
14.000 1.8323 0.02432 0.01844 -0.0584 0.0573 1.0000
14.250 1.8446 0.02510 0.01929 -0.0566 0.0559 1.0000
14.500 1.8552 0.02605 0.02028 -0.0546 0.0542 1.0000
14.750 1.8640 0.02718 0.02145 -0.0526 0.0524 1.0000
15.000 1.8695 0.02860 0.02292 -0.0505 0.0505 1.0000
15.250 1.8801 0.02968 0.02409 -0.0490 0.0495 1.0000
15.500 1.8893 0.03094 0.02541 -0.0475 0.0482 1.0000
15.750 1.8963 0.03242 0.02696 -0.0460 0.0467 1.0000
16.000 1.9007 0.03419 0.02877 -0.0445 0.0452 1.0000
16.250 1.9018 0.03635 0.03099 -0.0430 0.0435 1.0000
16.500 1.9092 0.03800 0.03274 -0.0421 0.0427 1.0000
16.750 1.9136 0.04000 0.03482 -0.0412 0.0417 1.0000
17.000 1.9156 0.04231 0.03721 -0.0404 0.0406 1.0000
17.250 1.9150 0.04499 0.03996 -0.0398 0.0396 1.0000
17.500 1.9116 0.04809 0.04313 -0.0393 0.0384 1.0000
17.750 1.9056 0.05161 0.04676 -0.0391 0.0374 1.0000
18.000 1.9054 0.05453 0.04979 -0.0391 0.0368 1.0000
18.250 1.9017 0.05801 0.05337 -0.0393 0.0360 1.0000
18.500 1.8953 0.06193 0.05740 -0.0398 0.0353 1.0000
18.750 1.8856 0.06643 0.06200 -0.0406 0.0347 1.0000
19.000 1.8728 0.07146 0.06714 -0.0418 0.0340 1.0000
19.250 1.8567 0.07714 0.07294 -0.0433 0.0334 1.0000
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