RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF-48 AIRFOIL (raf48-il) Reynolds number: 500,000 Max Cl/Cd: 97.77 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf48-il-500000.txt Download as CSV file: xf-raf48-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7767 0.10552 0.10252 -0.0428 1.0000 0.0248
-17.000 -0.8387 0.08965 0.08639 -0.0532 1.0000 0.0248
-16.750 -0.8747 0.07966 0.07622 -0.0597 1.0000 0.0247
-16.500 -0.9027 0.07124 0.06762 -0.0654 1.0000 0.0247
-16.250 -0.9261 0.06385 0.06005 -0.0707 1.0000 0.0248
-16.000 -0.9496 0.05703 0.05304 -0.0750 1.0000 0.0250
-15.750 -0.9616 0.05219 0.04808 -0.0779 1.0000 0.0252
-15.500 -0.9686 0.04826 0.04406 -0.0799 1.0000 0.0254
-15.250 -0.9710 0.04513 0.04087 -0.0815 1.0000 0.0257
-15.000 -0.9745 0.04208 0.03773 -0.0826 1.0000 0.0259
-14.750 -0.9753 0.03959 0.03515 -0.0832 1.0000 0.0262
-14.500 -0.9747 0.03749 0.03297 -0.0833 1.0000 0.0267
-14.250 -0.9752 0.03545 0.03084 -0.0829 1.0000 0.0271
-14.000 -0.9763 0.03354 0.02881 -0.0819 1.0000 0.0274
-13.750 -0.9754 0.03199 0.02714 -0.0804 1.0000 0.0279
-13.500 -0.9737 0.03077 0.02579 -0.0785 1.0000 0.0284
-13.250 -0.9726 0.02964 0.02451 -0.0760 1.0000 0.0288
-13.000 -0.9739 0.02814 0.02291 -0.0729 1.0000 0.0294
-12.750 -0.9707 0.02714 0.02189 -0.0699 1.0000 0.0299
-12.500 -0.9678 0.02641 0.02113 -0.0664 1.0000 0.0303
-12.250 -0.9655 0.02588 0.02059 -0.0625 1.0000 0.0309
-12.000 -0.9607 0.02527 0.01994 -0.0590 1.0000 0.0315
-11.750 -0.9594 0.02470 0.01932 -0.0548 1.0000 0.0319
-11.500 -0.9267 0.02374 0.01823 -0.0568 0.9948 0.0330
-11.250 -0.8964 0.02272 0.01706 -0.0583 0.9858 0.0340
-11.000 -0.8675 0.02153 0.01588 -0.0596 0.9760 0.0351
-10.750 -0.8325 0.02080 0.01512 -0.0618 0.9682 0.0363
-10.500 -0.7959 0.02003 0.01425 -0.0641 0.9588 0.0376
-10.250 -0.7561 0.01937 0.01345 -0.0671 0.9493 0.0388
-10.000 -0.7186 0.01811 0.01217 -0.0700 0.9380 0.0405
-9.750 -0.6829 0.01748 0.01147 -0.0721 0.9235 0.0419
-9.500 -0.6544 0.01698 0.01086 -0.0725 0.9070 0.0432
-9.250 -0.6306 0.01667 0.01040 -0.0718 0.8911 0.0446
-9.000 -0.6120 0.01603 0.00967 -0.0702 0.8765 0.0459
-8.750 -0.5928 0.01554 0.00913 -0.0687 0.8638 0.0473
-8.500 -0.5716 0.01519 0.00871 -0.0675 0.8530 0.0488
-8.250 -0.5502 0.01486 0.00831 -0.0662 0.8420 0.0504
-8.000 -0.5274 0.01462 0.00795 -0.0652 0.8324 0.0519
-7.750 -0.5091 0.01399 0.00730 -0.0635 0.8230 0.0542
-7.500 -0.4871 0.01366 0.00693 -0.0624 0.8142 0.0564
-7.250 -0.4642 0.01340 0.00658 -0.0614 0.8052 0.0588
-7.000 -0.4432 0.01297 0.00612 -0.0600 0.7959 0.0620
-6.750 -0.4206 0.01268 0.00578 -0.0589 0.7873 0.0656
-6.500 -0.3976 0.01238 0.00544 -0.0579 0.7790 0.0697
-6.250 -0.3747 0.01207 0.00512 -0.0569 0.7716 0.0758
-6.000 -0.3512 0.01179 0.00484 -0.0560 0.7653 0.0839
-5.750 -0.3274 0.01152 0.00461 -0.0552 0.7588 0.0942
-5.500 -0.3030 0.01130 0.00439 -0.0544 0.7530 0.1063
-5.250 -0.2782 0.01112 0.00421 -0.0537 0.7475 0.1185
-5.000 -0.2530 0.01096 0.00406 -0.0531 0.7414 0.1297
-4.750 -0.2282 0.01078 0.00389 -0.0525 0.7358 0.1414
-4.500 -0.2032 0.01062 0.00374 -0.0518 0.7305 0.1522
-4.250 -0.1779 0.01046 0.00359 -0.0513 0.7250 0.1634
-3.750 -0.1273 0.01018 0.00332 -0.0501 0.7147 0.1911
-3.500 -0.1024 0.00999 0.00321 -0.0494 0.7090 0.2091
-3.250 -0.0778 0.00980 0.00309 -0.0487 0.7034 0.2315
-3.000 -0.0527 0.00966 0.00299 -0.0481 0.6983 0.2585
-2.750 -0.0283 0.00945 0.00290 -0.0473 0.6930 0.2882
-2.500 -0.0041 0.00924 0.00280 -0.0466 0.6874 0.3213
-2.250 0.0192 0.00899 0.00270 -0.0456 0.6822 0.3692
-2.000 0.0412 0.00869 0.00264 -0.0444 0.6766 0.4334
-1.750 0.0631 0.00842 0.00258 -0.0431 0.6704 0.4947
-1.500 0.0848 0.00818 0.00251 -0.0417 0.6647 0.5554
-1.250 0.1057 0.00794 0.00250 -0.0401 0.6589 0.6196
-1.000 0.1275 0.00775 0.00250 -0.0386 0.6525 0.6771
-0.750 0.1504 0.00765 0.00249 -0.0373 0.6467 0.7244
-0.500 0.1740 0.00754 0.00252 -0.0362 0.6398 0.7640
-0.250 0.1988 0.00749 0.00253 -0.0352 0.6327 0.7948
0.000 0.2240 0.00748 0.00254 -0.0344 0.6255 0.8216
0.250 0.2500 0.00745 0.00255 -0.0337 0.6175 0.8451
0.500 0.2778 0.00745 0.00255 -0.0335 0.6101 0.8661
0.750 0.3083 0.00742 0.00257 -0.0338 0.6008 0.8860
1.000 0.3450 0.00746 0.00259 -0.0355 0.5914 0.9041
1.250 0.3898 0.00754 0.00266 -0.0390 0.5808 0.9191
1.500 0.4375 0.00767 0.00277 -0.0431 0.5692 0.9311
1.750 0.4779 0.00782 0.00286 -0.0456 0.5578 0.9398
2.000 0.5159 0.00800 0.00296 -0.0477 0.5460 0.9461
2.250 0.5483 0.00818 0.00311 -0.0485 0.5340 0.9557
2.500 0.5877 0.00840 0.00326 -0.0508 0.5213 0.9613
2.750 0.6200 0.00862 0.00341 -0.0517 0.5093 0.9701
3.000 0.6610 0.00883 0.00354 -0.0545 0.4970 0.9741
3.250 0.6973 0.00900 0.00368 -0.0563 0.4867 0.9796
3.500 0.7325 0.00919 0.00380 -0.0580 0.4771 0.9839
3.750 0.7703 0.00932 0.00390 -0.0602 0.4676 0.9872
4.000 0.8076 0.00948 0.00403 -0.0624 0.4588 0.9915
4.250 0.8473 0.00962 0.00413 -0.0651 0.4496 0.9952
4.500 0.8876 0.00972 0.00422 -0.0679 0.4418 0.9987
4.750 0.9153 0.00982 0.00430 -0.0682 0.4345 1.0000
5.000 0.9325 0.00996 0.00440 -0.0662 0.4283 1.0000
5.250 0.9512 0.01003 0.00450 -0.0646 0.4218 1.0000
5.500 0.9695 0.01018 0.00462 -0.0628 0.4157 1.0000
5.750 0.9890 0.01032 0.00477 -0.0613 0.4099 1.0000
6.000 1.0093 0.01044 0.00491 -0.0599 0.4034 1.0000
6.250 1.0284 0.01065 0.00509 -0.0582 0.3969 1.0000
6.500 1.0492 0.01077 0.00525 -0.0569 0.3891 1.0000
6.750 1.0677 0.01100 0.00543 -0.0552 0.3800 1.0000
7.000 1.0882 0.01113 0.00560 -0.0538 0.3698 1.0000
7.250 1.1070 0.01135 0.00581 -0.0521 0.3603 1.0000
7.500 1.1254 0.01157 0.00602 -0.0504 0.3487 1.0000
7.750 1.1439 0.01179 0.00623 -0.0487 0.3358 1.0000
8.000 1.1607 0.01207 0.00648 -0.0467 0.3208 1.0000
8.250 1.1755 0.01242 0.00678 -0.0444 0.3033 1.0000
8.500 1.1882 0.01284 0.00712 -0.0418 0.2852 1.0000
8.750 1.1992 0.01332 0.00752 -0.0388 0.2662 1.0000
9.000 1.2082 0.01382 0.00794 -0.0356 0.2491 1.0000
9.250 1.2125 0.01432 0.00838 -0.0314 0.2342 1.0000
9.500 1.2175 0.01485 0.00885 -0.0275 0.2213 1.0000
9.750 1.2248 0.01540 0.00937 -0.0242 0.2093 1.0000
10.000 1.2336 0.01598 0.00992 -0.0214 0.1980 1.0000
10.250 1.2421 0.01664 0.01056 -0.0186 0.1877 1.0000
10.500 1.2494 0.01743 0.01131 -0.0160 0.1772 1.0000
10.750 1.2603 0.01812 0.01201 -0.0139 0.1678 1.0000
11.000 1.2694 0.01896 0.01284 -0.0118 0.1585 1.0000
11.250 1.2765 0.01998 0.01382 -0.0097 0.1485 1.0000
11.500 1.2865 0.02089 0.01474 -0.0080 0.1388 1.0000
11.750 1.2945 0.02199 0.01583 -0.0063 0.1287 1.0000
12.000 1.3001 0.02330 0.01710 -0.0046 0.1162 1.0000
12.250 1.3037 0.02484 0.01858 -0.0029 0.1017 1.0000
12.500 1.3019 0.02684 0.02047 -0.0010 0.0829 1.0000
12.750 1.2989 0.02904 0.02258 0.0007 0.0680 1.0000
13.000 1.2971 0.03124 0.02475 0.0021 0.0593 1.0000
13.250 1.2976 0.03335 0.02687 0.0032 0.0545 1.0000
13.500 1.2961 0.03568 0.02921 0.0043 0.0507 1.0000
13.750 1.2973 0.03785 0.03145 0.0051 0.0484 1.0000
14.000 1.2994 0.04001 0.03367 0.0058 0.0463 1.0000
14.250 1.2975 0.04262 0.03631 0.0064 0.0442 1.0000
14.500 1.2937 0.04554 0.03928 0.0068 0.0424 1.0000
14.750 1.2966 0.04784 0.04168 0.0071 0.0412 1.0000
15.000 1.2973 0.05044 0.04436 0.0073 0.0398 1.0000
15.250 1.2957 0.05336 0.04734 0.0073 0.0387 1.0000
15.500 1.2902 0.05681 0.05084 0.0072 0.0375 1.0000
15.750 1.2829 0.06054 0.05463 0.0069 0.0365 1.0000
16.000 1.2843 0.06333 0.05752 0.0066 0.0357 1.0000
16.250 1.2848 0.06629 0.06056 0.0062 0.0344 1.0000
16.500 1.2822 0.06967 0.06403 0.0057 0.0337 1.0000
16.750 1.2786 0.07321 0.06763 0.0051 0.0329 1.0000
17.000 1.2717 0.07722 0.07168 0.0043 0.0320 1.0000
17.250 1.2639 0.08135 0.07587 0.0035 0.0312 1.0000
17.500 1.2642 0.08451 0.07912 0.0028 0.0307 1.0000
17.750 1.2625 0.08801 0.08272 0.0019 0.0298 1.0000
18.000 1.2603 0.09156 0.08635 0.0010 0.0292 1.0000
18.250 1.2575 0.09524 0.09008 0.0000 0.0284 1.0000
18.500 1.2540 0.09906 0.09395 -0.0012 0.0277 1.0000
18.750 1.2496 0.10286 0.09778 -0.0022 0.0272 1.0000
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