RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 38 AIRFOIL (raf38-il) Reynolds number: 500,000 Max Cl/Cd: 90.54 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf38-il-500000-n5.txt Download as CSV file: xf-raf38-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 38 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7122 0.12374 0.12094 -0.0233 1.0000 0.0109
-16.250 -0.7546 0.11079 0.10787 -0.0299 1.0000 0.0109
-16.000 -0.7926 0.09959 0.09659 -0.0358 1.0000 0.0108
-15.750 -0.8395 0.08744 0.08432 -0.0425 1.0000 0.0106
-15.500 -0.8913 0.07460 0.07132 -0.0499 1.0000 0.0105
-15.250 -0.9410 0.06181 0.05834 -0.0580 1.0000 0.0102
-15.000 -0.9754 0.05143 0.04774 -0.0657 1.0000 0.0101
-14.750 -0.9958 0.04421 0.04032 -0.0713 1.0000 0.0100
-14.500 -1.0088 0.03928 0.03521 -0.0746 1.0000 0.0102
-14.250 -1.0191 0.03566 0.03143 -0.0759 1.0000 0.0102
-14.000 -1.0227 0.03329 0.02893 -0.0756 1.0000 0.0104
-13.750 -1.0266 0.03129 0.02680 -0.0743 1.0000 0.0105
-13.500 -1.0273 0.02979 0.02518 -0.0722 1.0000 0.0107
-13.250 -1.0284 0.02849 0.02376 -0.0693 1.0000 0.0109
-13.000 -1.0290 0.02744 0.02259 -0.0658 1.0000 0.0111
-12.750 -1.0288 0.02630 0.02136 -0.0623 1.0000 0.0113
-12.500 -1.0236 0.02521 0.02020 -0.0595 1.0000 0.0116
-12.250 -1.0153 0.02426 0.01917 -0.0569 1.0000 0.0118
-12.000 -1.0053 0.02340 0.01821 -0.0545 1.0000 0.0121
-11.750 -0.9936 0.02263 0.01736 -0.0522 1.0000 0.0124
-11.500 -0.9818 0.02187 0.01651 -0.0499 1.0000 0.0128
-11.250 -0.9616 0.02106 0.01561 -0.0492 0.9985 0.0133
-11.000 -0.9329 0.02026 0.01469 -0.0502 0.9933 0.0138
-10.750 -0.9061 0.01932 0.01367 -0.0509 0.9871 0.0145
-10.500 -0.8784 0.01856 0.01286 -0.0515 0.9799 0.0153
-10.250 -0.8480 0.01787 0.01207 -0.0526 0.9730 0.0162
-10.000 -0.8158 0.01722 0.01131 -0.0540 0.9652 0.0171
-9.750 -0.7841 0.01646 0.01050 -0.0554 0.9553 0.0183
-9.500 -0.7497 0.01583 0.00980 -0.0572 0.9440 0.0197
-9.250 -0.7140 0.01525 0.00912 -0.0592 0.9297 0.0214
-9.000 -0.6801 0.01468 0.00850 -0.0608 0.9109 0.0239
-8.750 -0.6511 0.01428 0.00798 -0.0613 0.8885 0.0261
-8.500 -0.6253 0.01396 0.00759 -0.0610 0.8684 0.0289
-8.250 -0.6006 0.01372 0.00726 -0.0604 0.8518 0.0320
-8.000 -0.5761 0.01350 0.00697 -0.0598 0.8378 0.0349
-7.750 -0.5510 0.01335 0.00677 -0.0593 0.8255 0.0381
-7.250 -0.5010 0.01303 0.00625 -0.0581 0.8043 0.0425
-7.000 -0.4764 0.01280 0.00598 -0.0575 0.7958 0.0450
-6.750 -0.4509 0.01264 0.00578 -0.0571 0.7874 0.0473
-6.500 -0.4254 0.01249 0.00554 -0.0566 0.7797 0.0494
-6.250 -0.3996 0.01235 0.00533 -0.0562 0.7717 0.0512
-6.000 -0.3736 0.01224 0.00513 -0.0557 0.7646 0.0522
-5.750 -0.3494 0.01189 0.00474 -0.0551 0.7575 0.0545
-5.250 -0.2992 0.01145 0.00422 -0.0540 0.7411 0.0586
-5.000 -0.2739 0.01129 0.00397 -0.0534 0.7321 0.0604
-4.750 -0.2482 0.01112 0.00375 -0.0529 0.7229 0.0620
-4.500 -0.2224 0.01098 0.00353 -0.0525 0.7156 0.0632
-4.250 -0.1961 0.01082 0.00333 -0.0521 0.7090 0.0641
-4.000 -0.1706 0.01062 0.00308 -0.0516 0.7027 0.0665
-3.750 -0.1446 0.01045 0.00289 -0.0512 0.6969 0.0691
-3.500 -0.1183 0.01029 0.00272 -0.0508 0.6909 0.0723
-3.250 -0.0920 0.01018 0.00256 -0.0505 0.6852 0.0754
-3.000 -0.0656 0.01003 0.00241 -0.0501 0.6795 0.0810
-2.750 -0.0397 0.00985 0.00227 -0.0497 0.6732 0.0947
-2.250 0.0109 0.00936 0.00205 -0.0488 0.6626 0.1724
-2.000 0.0372 0.00923 0.00197 -0.0485 0.6568 0.1967
-1.750 0.0632 0.00911 0.00189 -0.0481 0.6512 0.2189
-1.250 0.1144 0.00872 0.00174 -0.0472 0.6391 0.2955
-1.000 0.1384 0.00843 0.00170 -0.0466 0.6339 0.3719
-0.750 0.1633 0.00820 0.00168 -0.0460 0.6281 0.4344
-0.500 0.1885 0.00806 0.00165 -0.0454 0.6218 0.4797
-0.250 0.2137 0.00792 0.00164 -0.0449 0.6157 0.5224
0.000 0.2379 0.00773 0.00163 -0.0441 0.6089 0.5788
0.250 0.2614 0.00757 0.00164 -0.0431 0.6028 0.6354
0.500 0.2861 0.00745 0.00167 -0.0423 0.5963 0.6823
0.750 0.3102 0.00735 0.00170 -0.0414 0.5893 0.7299
1.000 0.3340 0.00722 0.00175 -0.0404 0.5821 0.7843
1.250 0.3592 0.00711 0.00182 -0.0395 0.5739 0.8398
1.500 0.3917 0.00710 0.00193 -0.0403 0.5649 0.8900
1.750 0.4303 0.00719 0.00202 -0.0425 0.5521 0.9187
2.000 0.4680 0.00732 0.00210 -0.0445 0.5359 0.9374
2.250 0.5044 0.00746 0.00219 -0.0463 0.5189 0.9510
2.500 0.5410 0.00763 0.00228 -0.0482 0.4995 0.9598
2.750 0.5737 0.00781 0.00238 -0.0493 0.4821 0.9671
3.000 0.6039 0.00799 0.00249 -0.0498 0.4667 0.9742
3.250 0.6381 0.00815 0.00260 -0.0513 0.4541 0.9780
3.500 0.6698 0.00833 0.00273 -0.0522 0.4414 0.9831
3.750 0.7027 0.00853 0.00286 -0.0534 0.4256 0.9870
4.000 0.7365 0.00873 0.00301 -0.0549 0.4099 0.9910
4.250 0.7720 0.00890 0.00315 -0.0567 0.3984 0.9952
4.500 0.8109 0.00908 0.00330 -0.0593 0.3834 0.9992
4.750 0.8361 0.00928 0.00345 -0.0589 0.3676 1.0000
5.000 0.8569 0.00947 0.00361 -0.0576 0.3527 1.0000
5.250 0.8773 0.00969 0.00378 -0.0562 0.3360 1.0000
5.500 0.8960 0.01000 0.00399 -0.0545 0.3099 1.0000
5.750 0.9130 0.01042 0.00426 -0.0526 0.2772 1.0000
6.000 0.9295 0.01087 0.00457 -0.0506 0.2485 1.0000
6.250 0.9467 0.01129 0.00488 -0.0487 0.2264 1.0000
6.500 0.9641 0.01169 0.00521 -0.0468 0.2069 1.0000
6.750 0.9811 0.01211 0.00554 -0.0449 0.1857 1.0000
7.000 0.9965 0.01262 0.00593 -0.0428 0.1599 1.0000
7.250 1.0074 0.01336 0.00644 -0.0399 0.1183 1.0000
7.500 1.0176 0.01412 0.00701 -0.0370 0.0876 1.0000
7.750 1.0323 0.01463 0.00745 -0.0348 0.0767 1.0000
8.000 1.0490 0.01501 0.00785 -0.0329 0.0717 1.0000
8.250 1.0640 0.01546 0.00828 -0.0308 0.0671 1.0000
8.500 1.0802 0.01583 0.00868 -0.0288 0.0637 1.0000
8.750 1.0941 0.01623 0.00911 -0.0264 0.0608 1.0000
9.000 1.1055 0.01668 0.00957 -0.0237 0.0577 1.0000
9.250 1.1174 0.01713 0.01005 -0.0211 0.0549 1.0000
9.500 1.1319 0.01753 0.01049 -0.0190 0.0523 1.0000
9.750 1.1450 0.01802 0.01101 -0.0168 0.0489 1.0000
10.000 1.1567 0.01862 0.01161 -0.0146 0.0447 1.0000
10.250 1.1708 0.01915 0.01220 -0.0128 0.0418 1.0000
10.500 1.1825 0.01983 0.01287 -0.0109 0.0364 1.0000
10.750 1.1936 0.02060 0.01364 -0.0090 0.0319 1.0000
11.000 1.2032 0.02150 0.01453 -0.0071 0.0278 1.0000
11.250 1.2133 0.02243 0.01549 -0.0054 0.0250 1.0000
11.500 1.2220 0.02352 0.01660 -0.0038 0.0227 1.0000
11.750 1.2313 0.02462 0.01777 -0.0023 0.0209 1.0000
12.000 1.2399 0.02584 0.01903 -0.0009 0.0193 1.0000
12.250 1.2473 0.02720 0.02043 0.0003 0.0181 1.0000
12.500 1.2554 0.02856 0.02186 0.0015 0.0171 1.0000
12.750 1.2636 0.02996 0.02333 0.0025 0.0163 1.0000
13.000 1.2707 0.03149 0.02493 0.0034 0.0155 1.0000
13.250 1.2764 0.03319 0.02668 0.0042 0.0149 1.0000
13.500 1.2803 0.03510 0.02864 0.0050 0.0142 1.0000
13.750 1.2864 0.03687 0.03050 0.0057 0.0137 1.0000
14.000 1.2908 0.03882 0.03255 0.0063 0.0133 1.0000
14.250 1.2947 0.04087 0.03468 0.0067 0.0127 1.0000
14.500 1.2965 0.04319 0.03708 0.0071 0.0123 1.0000
14.750 1.2985 0.04554 0.03950 0.0074 0.0120 1.0000
15.000 1.2979 0.04824 0.04228 0.0075 0.0116 1.0000
15.250 1.2976 0.05103 0.04515 0.0075 0.0113 1.0000
15.500 1.2988 0.05371 0.04793 0.0073 0.0111 1.0000
15.750 1.2982 0.05666 0.05098 0.0071 0.0107 1.0000
16.000 1.2975 0.05972 0.05414 0.0067 0.0104 1.0000
16.250 1.2950 0.06310 0.05762 0.0061 0.0103 1.0000
16.500 1.2932 0.06645 0.06106 0.0054 0.0100 1.0000
16.750 1.2880 0.07033 0.06504 0.0044 0.0099 1.0000
17.000 1.2853 0.07397 0.06877 0.0035 0.0096 1.0000
17.250 1.2789 0.07820 0.07310 0.0023 0.0095 1.0000
17.500 1.2711 0.08269 0.07769 0.0009 0.0093 1.0000
17.750 1.2621 0.08747 0.08256 -0.0007 0.0092 1.0000
18.000 1.2548 0.09206 0.08726 -0.0023 0.0091 1.0000
18.250 1.2482 0.09659 0.09190 -0.0039 0.0090 1.0000
18.500 1.2404 0.10138 0.09681 -0.0058 0.0089 1.0000
18.750 1.2328 0.10627 0.10181 -0.0077 0.0087 1.0000
19.000 1.2238 0.11147 0.10712 -0.0099 0.0086 1.0000
19.250 1.2145 0.11675 0.11251 -0.0122 0.0085 1.0000
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