RAF 31 AIRFOIL (raf31-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 31 AIRFOIL (raf31-il) Reynolds number: 100,000 Max Cl/Cd: 50.31 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf31-il-100000-n5.txt Download as CSV file: xf-raf31-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 31 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5471 0.09259 0.08704 -0.0492 1.0000 0.0445
-11.750 -0.5952 0.07790 0.07235 -0.0584 1.0000 0.0440
-11.500 -0.6403 0.06681 0.06118 -0.0665 1.0000 0.0432
-11.250 -0.6762 0.05982 0.05403 -0.0709 1.0000 0.0428
-11.000 -0.7058 0.05527 0.04934 -0.0716 1.0000 0.0427
-10.750 -0.7327 0.05224 0.04616 -0.0691 1.0000 0.0427
-10.500 -0.7545 0.04948 0.04322 -0.0656 1.0000 0.0429
-10.250 -0.7694 0.04677 0.04026 -0.0623 1.0000 0.0433
-10.000 -0.7797 0.04421 0.03743 -0.0589 1.0000 0.0437
-9.750 -0.7861 0.04184 0.03476 -0.0555 1.0000 0.0441
-9.500 -0.7890 0.03971 0.03233 -0.0521 1.0000 0.0444
-9.250 -0.7892 0.03780 0.03011 -0.0487 1.0000 0.0449
-9.000 -0.7849 0.03612 0.02828 -0.0459 1.0000 0.0457
-8.750 -0.7771 0.03497 0.02708 -0.0435 1.0000 0.0466
-8.500 -0.7687 0.03388 0.02589 -0.0411 1.0000 0.0476
-8.250 -0.7398 0.03227 0.02406 -0.0425 0.9952 0.0489
-8.000 -0.7115 0.03062 0.02217 -0.0437 0.9901 0.0500
-7.750 -0.6817 0.02912 0.02045 -0.0449 0.9853 0.0512
-7.500 -0.6533 0.02780 0.01890 -0.0457 0.9797 0.0526
-7.250 -0.6230 0.02666 0.01759 -0.0468 0.9747 0.0545
-7.000 -0.5955 0.02573 0.01667 -0.0475 0.9686 0.0565
-6.750 -0.5652 0.02483 0.01570 -0.0486 0.9633 0.0585
-6.500 -0.5370 0.02395 0.01471 -0.0491 0.9575 0.0606
-6.250 -0.5081 0.02313 0.01377 -0.0497 0.9517 0.0632
-6.000 -0.4763 0.02228 0.01289 -0.0510 0.9476 0.0665
-5.750 -0.4512 0.02163 0.01220 -0.0509 0.9402 0.0709
-5.500 -0.4194 0.02090 0.01139 -0.0521 0.9357 0.0790
-5.250 -0.3905 0.02025 0.01070 -0.0527 0.9304 0.0913
-5.000 -0.3632 0.01954 0.01004 -0.0530 0.9245 0.1075
-4.750 -0.3305 0.01885 0.00942 -0.0544 0.9206 0.1301
-4.500 -0.3020 0.01828 0.00900 -0.0550 0.9150 0.1630
-4.250 -0.2739 0.01777 0.00864 -0.0554 0.9091 0.2086
-4.000 -0.2415 0.01724 0.00830 -0.0567 0.9051 0.2590
-3.750 -0.2160 0.01687 0.00815 -0.0565 0.8982 0.3187
-3.500 -0.1860 0.01654 0.00797 -0.0570 0.8922 0.3724
-3.250 -0.1536 0.01623 0.00776 -0.0578 0.8871 0.4194
-3.000 -0.1292 0.01605 0.00767 -0.0571 0.8787 0.4531
-2.750 -0.0956 0.01580 0.00748 -0.0580 0.8739 0.4885
-2.500 -0.0730 0.01571 0.00746 -0.0568 0.8649 0.5201
-2.250 -0.0416 0.01553 0.00733 -0.0572 0.8594 0.5569
-2.000 -0.0185 0.01545 0.00732 -0.0560 0.8509 0.5900
-1.750 0.0115 0.01529 0.00722 -0.0560 0.8446 0.6241
-1.500 0.0355 0.01521 0.00720 -0.0549 0.8358 0.6529
-1.250 0.0658 0.01507 0.00709 -0.0549 0.8292 0.6806
-1.000 0.0902 0.01504 0.00709 -0.0540 0.8212 0.7071
-0.750 0.1186 0.01496 0.00706 -0.0537 0.8151 0.7367
-0.500 0.1464 0.01491 0.00706 -0.0533 0.8088 0.7653
-0.250 0.1732 0.01486 0.00706 -0.0527 0.8014 0.7917
0.000 0.2055 0.01476 0.00696 -0.0531 0.7957 0.8172
0.250 0.2348 0.01473 0.00698 -0.0531 0.7866 0.8421
0.500 0.2725 0.01462 0.00687 -0.0546 0.7795 0.8667
0.750 0.3113 0.01460 0.00688 -0.0565 0.7703 0.8904
1.000 0.3549 0.01455 0.00683 -0.0594 0.7626 0.9119
1.250 0.3991 0.01455 0.00684 -0.0626 0.7540 0.9315
1.500 0.4432 0.01455 0.00683 -0.0658 0.7456 0.9498
1.750 0.4857 0.01452 0.00678 -0.0687 0.7359 0.9680
2.000 0.5257 0.01454 0.00680 -0.0712 0.7245 0.9869
2.250 0.5637 0.01455 0.00680 -0.0735 0.7141 1.0000
2.500 0.5843 0.01459 0.00680 -0.0721 0.7038 1.0000
2.750 0.6030 0.01470 0.00691 -0.0704 0.6922 1.0000
3.000 0.6240 0.01479 0.00698 -0.0690 0.6806 1.0000
3.250 0.6464 0.01487 0.00704 -0.0678 0.6689 1.0000
3.500 0.6678 0.01499 0.00717 -0.0665 0.6563 1.0000
3.750 0.6885 0.01512 0.00731 -0.0649 0.6422 1.0000
4.000 0.7095 0.01522 0.00737 -0.0634 0.6250 1.0000
4.250 0.7290 0.01533 0.00746 -0.0615 0.6044 1.0000
4.500 0.7479 0.01545 0.00755 -0.0595 0.5811 1.0000
4.750 0.7670 0.01560 0.00765 -0.0576 0.5565 1.0000
5.000 0.7863 0.01579 0.00775 -0.0557 0.5309 1.0000
5.250 0.8046 0.01604 0.00791 -0.0537 0.5029 1.0000
5.500 0.8226 0.01635 0.00810 -0.0516 0.4750 1.0000
5.750 0.8405 0.01674 0.00835 -0.0496 0.4495 1.0000
6.000 0.8581 0.01715 0.00869 -0.0477 0.4254 1.0000
6.250 0.8752 0.01760 0.00910 -0.0457 0.4008 1.0000
6.500 0.8913 0.01805 0.00953 -0.0436 0.3709 1.0000
6.750 0.9054 0.01855 0.00995 -0.0412 0.3262 1.0000
7.000 0.9139 0.01933 0.01040 -0.0379 0.2805 1.0000
7.250 0.9232 0.02019 0.01105 -0.0350 0.2489 1.0000
7.500 0.9354 0.02097 0.01178 -0.0325 0.2124 1.0000
7.750 0.9443 0.02189 0.01250 -0.0297 0.1778 1.0000
8.000 0.9520 0.02282 0.01327 -0.0266 0.1582 1.0000
8.250 0.9604 0.02373 0.01411 -0.0237 0.1457 1.0000
8.500 0.9681 0.02472 0.01502 -0.0209 0.1369 1.0000
8.750 0.9797 0.02556 0.01594 -0.0186 0.1297 1.0000
9.000 0.9890 0.02656 0.01695 -0.0161 0.1242 1.0000
9.250 1.0002 0.02753 0.01797 -0.0140 0.1187 1.0000
9.500 1.0120 0.02848 0.01898 -0.0121 0.1124 1.0000
9.750 1.0215 0.02962 0.02007 -0.0101 0.1067 1.0000
10.000 1.0339 0.03051 0.02110 -0.0085 0.0992 1.0000
10.250 1.0422 0.03167 0.02223 -0.0067 0.0928 1.0000
10.500 1.0541 0.03262 0.02336 -0.0052 0.0857 1.0000
10.750 1.0615 0.03389 0.02462 -0.0035 0.0806 1.0000
11.000 1.0733 0.03498 0.02589 -0.0022 0.0751 1.0000
11.250 1.0809 0.03628 0.02726 -0.0007 0.0697 1.0000
11.500 1.0892 0.03765 0.02877 0.0007 0.0639 1.0000
11.750 1.0954 0.03916 0.03035 0.0019 0.0583 1.0000
12.000 1.1009 0.04088 0.03220 0.0033 0.0531 1.0000
12.250 1.1051 0.04270 0.03411 0.0044 0.0481 1.0000
12.500 1.1081 0.04475 0.03623 0.0055 0.0446 1.0000
12.750 1.1119 0.04679 0.03840 0.0064 0.0406 1.0000
13.000 1.1121 0.04913 0.04077 0.0071 0.0383 1.0000
13.250 1.1151 0.05149 0.04329 0.0079 0.0359 1.0000
13.500 1.1166 0.05400 0.04593 0.0085 0.0341 1.0000
13.750 1.1164 0.05667 0.04870 0.0088 0.0327 1.0000
14.000 1.1147 0.05957 0.05167 0.0088 0.0316 1.0000
14.250 1.1138 0.06261 0.05489 0.0089 0.0304 1.0000
14.500 1.1120 0.06587 0.05834 0.0088 0.0294 1.0000
14.750 1.1083 0.06943 0.06208 0.0083 0.0283 1.0000
15.000 1.1036 0.07321 0.06599 0.0074 0.0275 1.0000
15.250 1.0985 0.07720 0.07013 0.0064 0.0271 1.0000
15.500 1.0917 0.08154 0.07459 0.0049 0.0264 1.0000
15.750 1.0847 0.08609 0.07925 0.0033 0.0260 1.0000
16.000 1.0768 0.09090 0.08417 0.0014 0.0257 1.0000
16.250 1.0655 0.09664 0.09011 -0.0011 0.0254 1.0000
16.500 1.0518 0.10305 0.09674 -0.0041 0.0253 1.0000
16.750 1.0342 0.11050 0.10441 -0.0080 0.0251 1.0000
17.000 1.0136 0.11900 0.11312 -0.0128 0.0251 1.0000
17.250 0.9901 0.12867 0.12300 -0.0184 0.0252 1.0000
17.500 0.9606 0.14056 0.13506 -0.0255 0.0254 1.0000
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