RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF-48 AIRFOIL (raf48-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.09 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf48-il-1000000-n5.txt Download as CSV file: xf-raf48-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.9800 0.09693 0.09403 -0.0456 1.0000 0.0131
-18.500 -1.0564 0.08123 0.07810 -0.0548 1.0000 0.0128
-18.250 -1.1308 0.06614 0.06274 -0.0639 1.0000 0.0125
-18.000 -1.1743 0.05560 0.05198 -0.0707 1.0000 0.0122
-17.750 -1.2031 0.04764 0.04383 -0.0761 1.0000 0.0125
-17.500 -1.2192 0.04205 0.03810 -0.0797 1.0000 0.0126
-17.250 -1.2276 0.03803 0.03395 -0.0818 1.0000 0.0126
-17.000 -1.2312 0.03497 0.03078 -0.0829 1.0000 0.0129
-16.750 -1.2331 0.03239 0.02810 -0.0834 1.0000 0.0132
-16.500 -1.2324 0.03029 0.02591 -0.0832 1.0000 0.0133
-16.250 -1.2298 0.02855 0.02409 -0.0825 1.0000 0.0135
-16.000 -1.2257 0.02708 0.02253 -0.0815 1.0000 0.0138
-15.750 -1.2202 0.02582 0.02120 -0.0801 1.0000 0.0140
-15.500 -1.2153 0.02464 0.01995 -0.0784 1.0000 0.0144
-15.250 -1.2089 0.02365 0.01891 -0.0764 1.0000 0.0149
-15.000 -1.2016 0.02279 0.01800 -0.0742 1.0000 0.0152
-14.750 -1.1934 0.02206 0.01722 -0.0718 1.0000 0.0157
-14.500 -1.1852 0.02142 0.01653 -0.0692 1.0000 0.0161
-13.500 -1.1125 0.01890 0.01384 -0.0651 0.9656 0.0184
-13.250 -1.0643 0.01815 0.01304 -0.0701 0.9536 0.0194
-13.000 -1.0129 0.01745 0.01224 -0.0757 0.9389 0.0202
-12.750 -0.9714 0.01679 0.01149 -0.0793 0.9161 0.0211
-12.500 -0.9491 0.01643 0.01101 -0.0786 0.8935 0.0218
-12.250 -0.9306 0.01613 0.01062 -0.0771 0.8762 0.0227
-12.000 -0.9126 0.01582 0.01022 -0.0754 0.8607 0.0232
-11.750 -0.8934 0.01555 0.00986 -0.0738 0.8465 0.0238
-11.500 -0.8747 0.01522 0.00944 -0.0723 0.8331 0.0242
-11.250 -0.8559 0.01487 0.00903 -0.0707 0.8207 0.0249
-11.000 -0.8358 0.01458 0.00868 -0.0693 0.8083 0.0257
-10.750 -0.8150 0.01430 0.00834 -0.0681 0.7959 0.0264
-10.500 -0.7935 0.01405 0.00801 -0.0669 0.7847 0.0271
-10.250 -0.7719 0.01382 0.00770 -0.0657 0.7741 0.0277
-10.000 -0.7493 0.01357 0.00738 -0.0647 0.7654 0.0282
-9.500 -0.7050 0.01299 0.00672 -0.0626 0.7500 0.0301
-9.250 -0.6819 0.01275 0.00643 -0.0617 0.7425 0.0309
-9.000 -0.6584 0.01252 0.00616 -0.0609 0.7362 0.0316
-8.750 -0.6342 0.01232 0.00590 -0.0601 0.7299 0.0324
-8.500 -0.6107 0.01209 0.00562 -0.0593 0.7232 0.0333
-8.250 -0.5868 0.01184 0.00535 -0.0585 0.7168 0.0345
-8.000 -0.5627 0.01163 0.00511 -0.0577 0.7096 0.0358
-7.750 -0.5384 0.01145 0.00487 -0.0570 0.7030 0.0368
-7.500 -0.5133 0.01126 0.00465 -0.0564 0.6968 0.0378
-7.250 -0.4888 0.01106 0.00442 -0.0556 0.6899 0.0393
-7.000 -0.4641 0.01087 0.00420 -0.0550 0.6838 0.0410
-6.750 -0.4387 0.01068 0.00400 -0.0544 0.6786 0.0427
-6.500 -0.4132 0.01053 0.00381 -0.0539 0.6738 0.0443
-6.000 -0.3626 0.01017 0.00343 -0.0527 0.6648 0.0498
-5.750 -0.3368 0.01001 0.00326 -0.0522 0.6603 0.0527
-5.500 -0.3114 0.00984 0.00309 -0.0516 0.6556 0.0565
-5.250 -0.2858 0.00969 0.00293 -0.0511 0.6510 0.0611
-5.000 -0.2600 0.00952 0.00278 -0.0506 0.6464 0.0675
-4.750 -0.2346 0.00934 0.00264 -0.0500 0.6411 0.0774
-4.500 -0.2091 0.00918 0.00251 -0.0495 0.6362 0.0874
-4.250 -0.1832 0.00904 0.00239 -0.0490 0.6319 0.0961
-4.000 -0.1566 0.00893 0.00229 -0.0487 0.6271 0.1034
-3.750 -0.1307 0.00881 0.00219 -0.0482 0.6217 0.1118
-3.500 -0.1044 0.00873 0.00210 -0.0477 0.6165 0.1189
-3.250 -0.0780 0.00862 0.00201 -0.0474 0.6103 0.1280
-3.000 -0.0519 0.00853 0.00193 -0.0469 0.6039 0.1368
-2.750 -0.0256 0.00845 0.00186 -0.0465 0.5981 0.1461
-2.500 0.0006 0.00834 0.00179 -0.0461 0.5917 0.1591
-2.250 0.0263 0.00825 0.00172 -0.0456 0.5849 0.1731
-2.000 0.0525 0.00815 0.00167 -0.0451 0.5784 0.1884
-1.750 0.0780 0.00805 0.00161 -0.0446 0.5703 0.2106
-1.500 0.1033 0.00794 0.00157 -0.0440 0.5620 0.2366
-1.250 0.1287 0.00787 0.00153 -0.0434 0.5522 0.2597
-1.000 0.1545 0.00780 0.00151 -0.0430 0.5430 0.2799
-0.750 0.1800 0.00777 0.00148 -0.0424 0.5334 0.2986
-0.500 0.2056 0.00771 0.00147 -0.0419 0.5229 0.3197
-0.250 0.2305 0.00766 0.00145 -0.0412 0.5118 0.3460
0.250 0.2782 0.00747 0.00146 -0.0396 0.4889 0.4360
0.500 0.3025 0.00741 0.00148 -0.0388 0.4792 0.4742
0.750 0.3266 0.00738 0.00150 -0.0380 0.4692 0.5089
1.000 0.3501 0.00727 0.00153 -0.0371 0.4607 0.5568
1.250 0.3721 0.00718 0.00157 -0.0358 0.4523 0.6144
1.500 0.3950 0.00708 0.00162 -0.0347 0.4457 0.6660
1.750 0.4175 0.00704 0.00168 -0.0335 0.4382 0.7094
2.000 0.4406 0.00702 0.00175 -0.0324 0.4309 0.7444
2.250 0.4624 0.00700 0.00183 -0.0311 0.4222 0.7856
2.500 0.4856 0.00703 0.00191 -0.0300 0.4149 0.8158
2.750 0.5105 0.00706 0.00198 -0.0293 0.4088 0.8355
3.000 0.5348 0.00712 0.00207 -0.0285 0.4018 0.8570
3.250 0.5615 0.00713 0.00214 -0.0282 0.3965 0.8777
3.500 0.5926 0.00717 0.00223 -0.0288 0.3907 0.8993
3.750 0.6423 0.00730 0.00240 -0.0338 0.3829 0.9211
4.000 0.7066 0.00747 0.00256 -0.0419 0.3731 0.9340
4.250 0.7545 0.00766 0.00272 -0.0464 0.3654 0.9431
4.500 0.7937 0.00783 0.00288 -0.0489 0.3577 0.9522
4.750 0.8244 0.00802 0.00304 -0.0496 0.3512 0.9641
5.000 0.8517 0.00816 0.00318 -0.0495 0.3454 0.9748
5.500 0.9131 0.00852 0.00350 -0.0509 0.3293 0.9859
5.750 0.9447 0.00874 0.00366 -0.0519 0.3170 0.9890
6.000 0.9739 0.00902 0.00387 -0.0525 0.2989 0.9921
6.250 1.0032 0.00936 0.00411 -0.0532 0.2777 0.9944
6.500 1.0335 0.00975 0.00437 -0.0541 0.2556 0.9966
6.750 1.0635 0.01017 0.00467 -0.0551 0.2327 0.9986
7.000 1.0935 0.01055 0.00497 -0.0560 0.2155 1.0000
7.250 1.1101 0.01089 0.00524 -0.0540 0.2022 1.0000
7.500 1.1268 0.01121 0.00552 -0.0520 0.1913 1.0000
7.750 1.1425 0.01157 0.00582 -0.0498 0.1796 1.0000
8.000 1.1584 0.01191 0.00611 -0.0477 0.1691 1.0000
8.250 1.1737 0.01225 0.00642 -0.0454 0.1593 1.0000
8.500 1.1871 0.01266 0.00677 -0.0429 0.1483 1.0000
8.750 1.2006 0.01302 0.00711 -0.0404 0.1403 1.0000
9.000 1.2108 0.01334 0.00741 -0.0372 0.1341 1.0000
9.250 1.2194 0.01367 0.00773 -0.0337 0.1276 1.0000
9.500 1.2292 0.01405 0.00809 -0.0306 0.1214 1.0000
9.750 1.2385 0.01450 0.00852 -0.0276 0.1136 1.0000
10.000 1.2490 0.01499 0.00899 -0.0249 0.1064 1.0000
10.250 1.2575 0.01561 0.00957 -0.0221 0.0976 1.0000
10.500 1.2652 0.01636 0.01027 -0.0194 0.0865 1.0000
10.750 1.2692 0.01736 0.01118 -0.0165 0.0707 1.0000
11.500 1.2894 0.02051 0.01425 -0.0101 0.0463 1.0000
11.750 1.2978 0.02161 0.01534 -0.0084 0.0421 1.0000
12.000 1.3088 0.02259 0.01636 -0.0071 0.0398 1.0000
12.500 1.3282 0.02486 0.01867 -0.0047 0.0357 1.0000
12.750 1.3384 0.02602 0.01987 -0.0037 0.0343 1.0000
13.000 1.3469 0.02735 0.02121 -0.0026 0.0326 1.0000
13.250 1.3553 0.02871 0.02261 -0.0017 0.0315 1.0000
13.500 1.3645 0.03004 0.02398 -0.0008 0.0304 1.0000
13.750 1.3726 0.03149 0.02547 0.0000 0.0292 1.0000
14.000 1.3795 0.03306 0.02709 0.0008 0.0281 1.0000
14.250 1.3857 0.03473 0.02879 0.0015 0.0272 1.0000
14.500 1.3918 0.03644 0.03055 0.0022 0.0263 1.0000
14.750 1.3988 0.03814 0.03230 0.0027 0.0256 1.0000
15.000 1.4044 0.03999 0.03421 0.0032 0.0248 1.0000
15.250 1.4085 0.04203 0.03629 0.0036 0.0236 1.0000
15.500 1.4124 0.04414 0.03845 0.0040 0.0230 1.0000
15.750 1.4159 0.04634 0.04070 0.0043 0.0220 1.0000
16.000 1.4195 0.04858 0.04300 0.0044 0.0214 1.0000
16.250 1.4222 0.05097 0.04545 0.0045 0.0207 1.0000
16.500 1.4228 0.05364 0.04816 0.0045 0.0195 1.0000
16.750 1.4239 0.05631 0.05089 0.0044 0.0191 1.0000
17.000 1.4248 0.05903 0.05367 0.0042 0.0183 1.0000
17.250 1.4251 0.06188 0.05659 0.0040 0.0177 1.0000
17.500 1.4239 0.06497 0.05974 0.0036 0.0168 1.0000
17.750 1.4211 0.06830 0.06313 0.0031 0.0160 1.0000
18.000 1.4182 0.07168 0.06657 0.0025 0.0156 1.0000
18.250 1.4161 0.07500 0.06997 0.0018 0.0152 1.0000
18.500 1.4131 0.07848 0.07352 0.0011 0.0147 1.0000
18.750 1.4090 0.08217 0.07728 0.0003 0.0142 1.0000
19.000 1.4038 0.08601 0.08119 -0.0007 0.0139 1.0000
19.250 1.3975 0.09005 0.08530 -0.0018 0.0134 1.0000
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