RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 38 AIRFOIL (raf38-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.93 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf38-il-1000000-n5.txt Download as CSV file: xf-raf38-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8779 0.10138 0.09891 -0.0342 1.0000 0.0076
-16.750 -0.9880 0.07869 0.07592 -0.0473 1.0000 0.0071
-16.500 -1.0887 0.05683 0.05370 -0.0613 1.0000 0.0068
-16.250 -1.1299 0.04563 0.04224 -0.0701 1.0000 0.0068
-16.000 -1.1428 0.04018 0.03663 -0.0741 1.0000 0.0068
-15.750 -1.1553 0.03574 0.03204 -0.0766 1.0000 0.0068
-15.500 -1.1582 0.03304 0.02921 -0.0772 1.0000 0.0069
-15.250 -1.1639 0.03054 0.02659 -0.0768 1.0000 0.0070
-15.000 -1.1676 0.02857 0.02451 -0.0754 1.0000 0.0071
-14.750 -1.1681 0.02709 0.02293 -0.0733 1.0000 0.0072
-14.500 -1.1680 0.02583 0.02159 -0.0705 1.0000 0.0073
-14.250 -1.1662 0.02487 0.02054 -0.0673 1.0000 0.0074
-14.000 -1.1631 0.02403 0.01963 -0.0639 1.0000 0.0075
-13.750 -1.1544 0.02317 0.01869 -0.0614 1.0000 0.0077
-13.500 -1.1439 0.02239 0.01784 -0.0591 1.0000 0.0078
-13.250 -1.1325 0.02164 0.01702 -0.0569 1.0000 0.0080
-13.000 -1.1201 0.02094 0.01625 -0.0546 1.0000 0.0082
-12.750 -1.1067 0.02031 0.01555 -0.0525 1.0000 0.0084
-12.250 -1.0586 0.01891 0.01400 -0.0525 0.9962 0.0088
-12.000 -1.0341 0.01813 0.01316 -0.0526 0.9910 0.0092
-11.750 -1.0071 0.01742 0.01238 -0.0531 0.9859 0.0095
-11.500 -0.9798 0.01679 0.01170 -0.0536 0.9795 0.0100
-11.250 -0.9482 0.01620 0.01106 -0.0549 0.9734 0.0105
-11.000 -0.9135 0.01562 0.01041 -0.0568 0.9661 0.0109
-10.750 -0.8769 0.01500 0.00972 -0.0592 0.9559 0.0115
-10.500 -0.8381 0.01436 0.00901 -0.0620 0.9400 0.0122
-10.250 -0.8050 0.01390 0.00844 -0.0635 0.9110 0.0129
-10.000 -0.7808 0.01361 0.00800 -0.0628 0.8775 0.0136
-9.750 -0.7593 0.01331 0.00756 -0.0617 0.8520 0.0144
-9.500 -0.7374 0.01298 0.00714 -0.0607 0.8347 0.0153
-9.250 -0.7145 0.01268 0.00676 -0.0598 0.8213 0.0164
-9.000 -0.6912 0.01241 0.00640 -0.0590 0.8098 0.0174
-8.750 -0.6680 0.01209 0.00603 -0.0581 0.7990 0.0189
-8.500 -0.6440 0.01181 0.00570 -0.0574 0.7893 0.0206
-8.250 -0.6200 0.01154 0.00538 -0.0567 0.7806 0.0228
-8.000 -0.5954 0.01126 0.00508 -0.0562 0.7727 0.0256
-7.750 -0.5708 0.01103 0.00483 -0.0556 0.7653 0.0291
-7.500 -0.5453 0.01082 0.00461 -0.0551 0.7583 0.0323
-7.250 -0.5199 0.01064 0.00442 -0.0546 0.7508 0.0357
-7.000 -0.4939 0.01049 0.00427 -0.0543 0.7441 0.0390
-6.750 -0.4676 0.01037 0.00410 -0.0539 0.7370 0.0408
-6.500 -0.4413 0.01027 0.00394 -0.0536 0.7301 0.0417
-6.250 -0.4157 0.01008 0.00371 -0.0531 0.7216 0.0440
-6.000 -0.3897 0.00993 0.00354 -0.0527 0.7133 0.0460
-5.750 -0.3635 0.00981 0.00339 -0.0523 0.7043 0.0479
-5.500 -0.3372 0.00970 0.00323 -0.0520 0.6963 0.0494
-5.250 -0.3107 0.00960 0.00308 -0.0517 0.6880 0.0507
-5.000 -0.2839 0.00951 0.00294 -0.0514 0.6820 0.0516
-4.750 -0.2569 0.00942 0.00283 -0.0512 0.6762 0.0522
-4.500 -0.2306 0.00927 0.00263 -0.0508 0.6703 0.0537
-4.250 -0.2042 0.00911 0.00245 -0.0504 0.6651 0.0558
-4.000 -0.1775 0.00898 0.00230 -0.0502 0.6592 0.0573
-3.750 -0.1508 0.00887 0.00217 -0.0499 0.6536 0.0588
-3.500 -0.1239 0.00877 0.00204 -0.0496 0.6491 0.0602
-3.250 -0.0967 0.00867 0.00194 -0.0494 0.6440 0.0616
-3.000 -0.0697 0.00860 0.00183 -0.0492 0.6383 0.0631
-2.750 -0.0427 0.00853 0.00174 -0.0489 0.6332 0.0646
-2.500 -0.0156 0.00843 0.00164 -0.0487 0.6275 0.0690
-2.250 0.0113 0.00834 0.00155 -0.0485 0.6220 0.0740
-2.000 0.0378 0.00821 0.00147 -0.0482 0.6172 0.0892
-1.750 0.0633 0.00794 0.00137 -0.0477 0.6121 0.1373
-1.500 0.0894 0.00778 0.00131 -0.0474 0.6061 0.1705
-1.250 0.1160 0.00769 0.00127 -0.0471 0.6004 0.1911
-1.000 0.1430 0.00761 0.00123 -0.0469 0.5940 0.2088
-0.750 0.1693 0.00751 0.00119 -0.0466 0.5879 0.2351
-0.500 0.1953 0.00733 0.00115 -0.0462 0.5823 0.2773
-0.250 0.2210 0.00716 0.00113 -0.0458 0.5756 0.3282
0.000 0.2461 0.00698 0.00111 -0.0453 0.5688 0.3884
0.250 0.2717 0.00682 0.00111 -0.0448 0.5607 0.4435
0.500 0.2970 0.00670 0.00112 -0.0443 0.5526 0.4930
0.750 0.3228 0.00664 0.00113 -0.0439 0.5413 0.5267
1.000 0.3482 0.00660 0.00114 -0.0434 0.5276 0.5613
1.250 0.3728 0.00656 0.00117 -0.0427 0.5114 0.6030
1.500 0.3955 0.00646 0.00122 -0.0416 0.4941 0.6708
1.750 0.4181 0.00641 0.00129 -0.0405 0.4770 0.7302
2.000 0.4401 0.00639 0.00137 -0.0392 0.4581 0.7841
2.250 0.4625 0.00637 0.00146 -0.0379 0.4426 0.8337
2.500 0.4875 0.00634 0.00156 -0.0372 0.4314 0.8840
2.750 0.5189 0.00641 0.00168 -0.0379 0.4213 0.9199
3.000 0.5566 0.00657 0.00182 -0.0400 0.4084 0.9426
3.250 0.5960 0.00673 0.00195 -0.0426 0.3968 0.9565
3.500 0.6318 0.00688 0.00207 -0.0444 0.3860 0.9652
3.750 0.6656 0.00704 0.00218 -0.0458 0.3730 0.9697
4.000 0.6951 0.00721 0.00231 -0.0462 0.3611 0.9753
4.250 0.7275 0.00740 0.00244 -0.0473 0.3461 0.9784
4.500 0.7565 0.00765 0.00260 -0.0477 0.3211 0.9828
4.750 0.7875 0.00796 0.00279 -0.0487 0.2940 0.9865
5.000 0.8198 0.00836 0.00303 -0.0500 0.2611 0.9902
5.250 0.8501 0.00883 0.00333 -0.0509 0.2279 0.9942
5.500 0.8841 0.00918 0.00358 -0.0526 0.2055 0.9969
5.750 0.9170 0.00953 0.00383 -0.0540 0.1839 0.9991
6.000 0.9424 0.00993 0.00411 -0.0539 0.1589 1.0000
6.250 0.9581 0.01040 0.00443 -0.0517 0.1292 1.0000
6.500 0.9698 0.01108 0.00488 -0.0488 0.0895 1.0000
6.750 0.9861 0.01151 0.00522 -0.0467 0.0737 1.0000
7.000 1.0042 0.01184 0.00552 -0.0450 0.0666 1.0000
7.250 1.0237 0.01209 0.00577 -0.0434 0.0634 1.0000
7.500 1.0427 0.01237 0.00604 -0.0418 0.0601 1.0000
7.750 1.0612 0.01267 0.00634 -0.0402 0.0568 1.0000
8.000 1.0805 0.01293 0.00661 -0.0387 0.0548 1.0000
8.250 1.0999 0.01317 0.00688 -0.0372 0.0528 1.0000
8.500 1.1184 0.01347 0.00717 -0.0356 0.0500 1.0000
8.750 1.1354 0.01382 0.00752 -0.0337 0.0462 1.0000
9.000 1.1534 0.01412 0.00783 -0.0321 0.0440 1.0000
9.250 1.1706 0.01445 0.00817 -0.0303 0.0402 1.0000
9.500 1.1828 0.01487 0.00855 -0.0276 0.0343 1.0000
10.000 1.2046 0.01578 0.00944 -0.0219 0.0252 1.0000
10.250 1.2156 0.01633 0.00997 -0.0193 0.0218 1.0000
10.500 1.2286 0.01685 0.01051 -0.0172 0.0199 1.0000
11.000 1.2530 0.01808 0.01178 -0.0131 0.0165 1.0000
11.250 1.2655 0.01875 0.01247 -0.0113 0.0154 1.0000
11.500 1.2769 0.01953 0.01328 -0.0095 0.0142 1.0000
11.750 1.2896 0.02028 0.01408 -0.0080 0.0136 1.0000
12.000 1.3013 0.02114 0.01497 -0.0065 0.0127 1.0000
12.250 1.3123 0.02210 0.01597 -0.0051 0.0120 1.0000
12.500 1.3227 0.02316 0.01707 -0.0038 0.0114 1.0000
12.750 1.3343 0.02417 0.01813 -0.0028 0.0109 1.0000
13.000 1.3448 0.02530 0.01931 -0.0017 0.0104 1.0000
13.250 1.3547 0.02653 0.02060 -0.0007 0.0101 1.0000
13.500 1.3634 0.02788 0.02200 0.0002 0.0098 1.0000
13.750 1.3708 0.02939 0.02356 0.0011 0.0093 1.0000
14.000 1.3788 0.03088 0.02511 0.0019 0.0090 1.0000
14.250 1.3869 0.03240 0.02669 0.0026 0.0086 1.0000
14.500 1.3931 0.03413 0.02848 0.0032 0.0084 1.0000
14.750 1.3997 0.03585 0.03027 0.0038 0.0081 1.0000
15.000 1.4044 0.03778 0.03225 0.0043 0.0079 1.0000
15.250 1.4079 0.03986 0.03440 0.0047 0.0076 1.0000
15.500 1.4107 0.04209 0.03669 0.0051 0.0075 1.0000
15.750 1.4111 0.04460 0.03928 0.0053 0.0073 1.0000
16.000 1.4139 0.04695 0.04171 0.0054 0.0071 1.0000
16.250 1.4153 0.04950 0.04435 0.0054 0.0070 1.0000
16.500 1.4161 0.05221 0.04713 0.0053 0.0069 1.0000
16.750 1.4164 0.05501 0.05002 0.0050 0.0067 1.0000
17.000 1.4157 0.05802 0.05311 0.0047 0.0066 1.0000
17.250 1.4147 0.06115 0.05632 0.0042 0.0064 1.0000
17.500 1.4125 0.06446 0.05971 0.0035 0.0063 1.0000
17.750 1.4077 0.06819 0.06353 0.0027 0.0062 1.0000
18.000 1.4045 0.07177 0.06719 0.0019 0.0061 1.0000
18.250 1.3976 0.07595 0.07147 0.0008 0.0060 1.0000
18.500 1.3924 0.07991 0.07551 -0.0004 0.0059 1.0000
18.750 1.3829 0.08458 0.08027 -0.0018 0.0058 1.0000
19.000 1.3735 0.08933 0.08512 -0.0033 0.0057 1.0000
19.250 1.3602 0.09473 0.09062 -0.0052 0.0056 1.0000
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