RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF-48 AIRFOIL (raf48-il) Reynolds number: 50,000 Max Cl/Cd: 25.79 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf48-il-50000-n5.txt Download as CSV file: xf-raf48-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF-48 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4049 0.10372 0.09603 -0.0471 1.0000 0.0857
-11.250 -0.4144 0.09832 0.09070 -0.0495 1.0000 0.0865
-11.000 -0.4292 0.09204 0.08449 -0.0526 1.0000 0.0872
-10.750 -0.4520 0.08419 0.07675 -0.0569 1.0000 0.0874
-10.500 -0.4916 0.07419 0.06680 -0.0633 1.0000 0.0869
-10.250 -0.5348 0.06739 0.06002 -0.0659 1.0000 0.0863
-10.000 -0.5754 0.06338 0.05602 -0.0635 1.0000 0.0858
-9.750 -0.6114 0.06048 0.05311 -0.0592 1.0000 0.0857
-9.500 -0.6425 0.05806 0.05064 -0.0543 1.0000 0.0857
-9.250 -0.6707 0.05597 0.04843 -0.0490 1.0000 0.0860
-9.000 -0.6941 0.05386 0.04614 -0.0440 1.0000 0.0865
-8.750 -0.7003 0.05042 0.04228 -0.0424 0.9941 0.0878
-8.500 -0.6876 0.04659 0.03784 -0.0436 0.9832 0.0903
-8.250 -0.6617 0.04511 0.03634 -0.0448 0.9743 0.0934
-8.000 -0.6399 0.04304 0.03397 -0.0456 0.9653 0.0971
-7.750 -0.6168 0.04041 0.03079 -0.0466 0.9573 0.1009
-7.500 -0.5938 0.03884 0.02904 -0.0469 0.9483 0.1048
-7.250 -0.5626 0.03750 0.02755 -0.0485 0.9420 0.1103
-7.000 -0.5409 0.03590 0.02548 -0.0482 0.9330 0.1159
-6.750 -0.5078 0.03482 0.02445 -0.0498 0.9272 0.1223
-6.500 -0.4832 0.03368 0.02298 -0.0497 0.9189 0.1304
-6.250 -0.4515 0.03274 0.02208 -0.0510 0.9127 0.1389
-6.000 -0.4209 0.03177 0.02098 -0.0519 0.9063 0.1499
-5.750 -0.3932 0.03102 0.02005 -0.0522 0.8986 0.1627
-5.500 -0.3570 0.03019 0.01917 -0.0540 0.8936 0.1782
-5.250 -0.3359 0.02970 0.01872 -0.0531 0.8844 0.1922
-5.000 -0.3023 0.02906 0.01799 -0.0543 0.8784 0.2117
-4.750 -0.2794 0.02865 0.01761 -0.0537 0.8696 0.2298
-4.500 -0.2485 0.02810 0.01712 -0.0544 0.8626 0.2524
-4.250 -0.2237 0.02769 0.01671 -0.0540 0.8539 0.2759
-4.000 -0.1936 0.02714 0.01622 -0.0544 0.8462 0.3036
-3.750 -0.1688 0.02670 0.01583 -0.0540 0.8375 0.3333
-3.500 -0.1413 0.02618 0.01545 -0.0538 0.8295 0.3693
-3.250 -0.1196 0.02577 0.01525 -0.0527 0.8208 0.4103
-3.000 -0.0964 0.02534 0.01505 -0.0515 0.8126 0.4650
-2.750 -0.0752 0.02500 0.01500 -0.0499 0.8045 0.5302
-2.250 -0.0136 0.02458 0.01514 -0.0485 0.7908 0.6961
-2.000 0.0149 0.02480 0.01544 -0.0477 0.7812 0.7612
-1.750 0.0654 0.02486 0.01542 -0.0503 0.7758 0.8197
-1.500 0.1056 0.02517 0.01563 -0.0519 0.7672 0.8644
-1.250 0.1694 0.02530 0.01557 -0.0574 0.7608 0.8990
-1.000 0.2370 0.02536 0.01542 -0.0640 0.7547 0.9239
-0.750 0.2877 0.02551 0.01543 -0.0683 0.7454 0.9474
-0.500 0.3469 0.02531 0.01504 -0.0739 0.7394 0.9684
-0.250 0.4023 0.02534 0.01497 -0.0798 0.7290 0.9911
0.000 0.4440 0.02507 0.01456 -0.0827 0.7221 1.0000
0.250 0.4527 0.02538 0.01483 -0.0801 0.7107 1.0000
0.500 0.4742 0.02528 0.01460 -0.0790 0.7038 1.0000
0.750 0.4814 0.02571 0.01500 -0.0762 0.6922 1.0000
1.000 0.5015 0.02572 0.01492 -0.0748 0.6851 1.0000
1.250 0.5100 0.02616 0.01533 -0.0720 0.6742 1.0000
1.500 0.5288 0.02628 0.01537 -0.0704 0.6667 1.0000
1.750 0.5390 0.02673 0.01579 -0.0678 0.6566 1.0000
2.000 0.5582 0.02690 0.01589 -0.0663 0.6493 1.0000
2.250 0.5685 0.02741 0.01639 -0.0637 0.6394 1.0000
2.500 0.5894 0.02756 0.01647 -0.0624 0.6325 1.0000
2.750 0.5986 0.02819 0.01709 -0.0597 0.6226 1.0000
3.000 0.6251 0.02817 0.01701 -0.0590 0.6171 1.0000
3.250 0.6293 0.02905 0.01791 -0.0557 0.6062 1.0000
3.500 0.6571 0.02900 0.01780 -0.0552 0.6009 1.0000
3.750 0.6599 0.03001 0.01884 -0.0519 0.5902 1.0000
4.000 0.6880 0.02996 0.01875 -0.0514 0.5847 1.0000
4.250 0.6910 0.03100 0.01983 -0.0480 0.5743 1.0000
4.500 0.7190 0.03095 0.01975 -0.0475 0.5686 1.0000
4.750 0.7224 0.03200 0.02084 -0.0443 0.5584 1.0000
5.000 0.7510 0.03190 0.02074 -0.0438 0.5524 1.0000
5.250 0.7542 0.03296 0.02184 -0.0405 0.5421 1.0000
5.500 0.7847 0.03274 0.02163 -0.0402 0.5359 1.0000
5.750 0.7865 0.03387 0.02280 -0.0368 0.5254 1.0000
6.000 0.8198 0.03350 0.02244 -0.0368 0.5192 1.0000
6.250 0.8192 0.03475 0.02374 -0.0332 0.5084 1.0000
6.500 0.8570 0.03414 0.02316 -0.0335 0.5022 1.0000
6.750 0.8531 0.03556 0.02464 -0.0297 0.4910 1.0000
7.000 0.8891 0.03501 0.02411 -0.0298 0.4840 1.0000
7.250 0.8882 0.03628 0.02546 -0.0263 0.4732 1.0000
7.500 0.9072 0.03658 0.02582 -0.0248 0.4643 1.0000
7.750 0.9250 0.03690 0.02619 -0.0231 0.4549 1.0000
8.000 0.9274 0.03796 0.02731 -0.0200 0.4448 1.0000
8.250 0.9641 0.03739 0.02679 -0.0201 0.4362 1.0000
8.500 0.9520 0.03920 0.02867 -0.0157 0.4249 1.0000
8.750 0.9857 0.03874 0.02825 -0.0155 0.4162 1.0000
9.000 0.9825 0.04019 0.02978 -0.0123 0.4050 1.0000
9.250 0.9830 0.04162 0.03129 -0.0097 0.3941 1.0000
9.500 1.0176 0.04097 0.03069 -0.0093 0.3851 1.0000
9.750 0.9993 0.04373 0.03356 -0.0060 0.3729 1.0000
10.000 1.0052 0.04502 0.03492 -0.0042 0.3624 1.0000
10.250 1.0281 0.04501 0.03497 -0.0031 0.3527 1.0000
10.500 1.0105 0.04833 0.03840 -0.0009 0.3409 1.0000
10.750 1.0205 0.04947 0.03962 0.0004 0.3312 1.0000
11.000 1.0339 0.05024 0.04046 0.0016 0.3214 1.0000
11.250 1.0169 0.05412 0.04444 0.0028 0.3103 1.0000
11.500 1.0439 0.05360 0.04396 0.0040 0.3022 1.0000
11.750 1.0337 0.05694 0.04741 0.0048 0.2918 1.0000
12.000 1.0266 0.06019 0.05074 0.0054 0.2822 1.0000
12.250 1.0586 0.05890 0.04950 0.0069 0.2740 1.0000
12.500 1.0300 0.06479 0.05550 0.0067 0.2637 1.0000
12.750 1.0475 0.06484 0.05557 0.0079 0.2537 1.0000
13.000 1.0752 0.06337 0.05402 0.0095 0.2418 1.0000
13.250 1.0409 0.07038 0.06122 0.0085 0.2325 1.0000
13.500 1.0490 0.07162 0.06247 0.0092 0.2222 1.0000
13.750 1.0715 0.07077 0.06154 0.0107 0.2110 1.0000
14.250 1.0512 0.07902 0.07000 0.0096 0.1934 1.0000
14.500 1.0346 0.08446 0.07557 0.0083 0.1849 1.0000
14.750 1.0291 0.08823 0.07941 0.0077 0.1763 1.0000
15.000 1.0450 0.08838 0.07953 0.0086 0.1668 1.0000
15.250 1.0063 0.09828 0.08964 0.0049 0.1598 1.0000
15.500 1.0308 0.09681 0.08808 0.0065 0.1506 1.0000
15.750 0.9797 0.10968 0.10119 0.0010 0.1438 1.0000
16.000 1.0062 0.10772 0.09917 0.0029 0.1359 1.0000
16.250 0.9446 0.12376 0.11537 -0.0046 0.1290 1.0000
16.500 0.9849 0.11866 0.11023 -0.0012 0.1227 1.0000
16.750 0.9070 0.13990 0.13153 -0.0117 0.1156 1.0000
17.000 0.9495 0.13360 0.12529 -0.0078 0.1114 1.0000
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