RAF 31 AIRFOIL (raf31-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: RAF 31 AIRFOIL (raf31-il) Reynolds number: 50,000 Max Cl/Cd: 33.81 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf31-il-50000.txt Download as CSV file: xf-raf31-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3701 0.10284 0.09534 -0.0219 1.0000 0.3345
-8.750 -0.3895 0.10122 0.09387 -0.0216 1.0000 0.3420
-8.500 -0.4362 0.09110 0.08395 -0.0314 1.0000 0.2488
-8.250 -0.5501 0.07359 0.06675 -0.0445 1.0000 0.1665
-8.000 -0.5719 0.06882 0.06203 -0.0436 1.0000 0.1611
-7.750 -0.6282 0.06210 0.05501 -0.0424 1.0000 0.1529
-7.500 -0.6341 0.05850 0.05132 -0.0403 1.0000 0.1507
-7.250 -0.6432 0.05459 0.04719 -0.0381 1.0000 0.1484
-7.000 -0.6507 0.05054 0.04276 -0.0360 1.0000 0.1460
-6.750 -0.6518 0.04685 0.03863 -0.0339 1.0000 0.1446
-6.500 -0.6461 0.04400 0.03545 -0.0319 1.0000 0.1456
-6.250 -0.6373 0.04151 0.03262 -0.0300 1.0000 0.1480
-6.000 -0.6266 0.03911 0.02978 -0.0282 1.0000 0.1507
-5.750 -0.6134 0.03681 0.02696 -0.0265 1.0000 0.1534
-5.500 -0.5968 0.03473 0.02464 -0.0251 1.0000 0.1567
-5.250 -0.5785 0.03313 0.02295 -0.0237 1.0000 0.1619
-5.000 -0.5600 0.03158 0.02103 -0.0222 1.0000 0.1700
-4.750 -0.5414 0.03033 0.01976 -0.0209 1.0000 0.1830
-4.500 -0.5222 0.02899 0.01838 -0.0194 1.0000 0.2002
-4.250 -0.5037 0.02756 0.01718 -0.0178 1.0000 0.2293
-4.000 -0.4874 0.02641 0.01637 -0.0159 1.0000 0.2760
-3.750 -0.4725 0.02564 0.01602 -0.0139 1.0000 0.3387
-3.500 -0.4608 0.02517 0.01602 -0.0109 1.0000 0.4193
-3.250 -0.4505 0.02491 0.01623 -0.0071 1.0000 0.4973
-3.000 -0.4388 0.02480 0.01636 -0.0033 1.0000 0.5610
-2.750 -0.4261 0.02474 0.01639 0.0001 1.0000 0.6153
-2.500 -0.4131 0.02470 0.01645 0.0036 1.0000 0.6625
-2.250 -0.4002 0.02465 0.01646 0.0071 1.0000 0.7069
-2.000 -0.3884 0.02457 0.01645 0.0108 1.0000 0.7544
-1.750 -0.3777 0.02445 0.01643 0.0151 1.0000 0.8107
-1.500 -0.3493 0.02453 0.01666 0.0166 1.0000 0.8835
-1.250 -0.2107 0.02637 0.01808 -0.0035 1.0000 0.9688
-1.000 -0.1661 0.02602 0.01745 -0.0116 1.0000 1.0000
-0.750 -0.1800 0.02507 0.01633 -0.0082 1.0000 1.0000
-0.500 -0.1730 0.02498 0.01598 -0.0071 1.0000 1.0000
-0.250 -0.1599 0.02520 0.01597 -0.0065 1.0000 1.0000
0.000 -0.1448 0.02556 0.01612 -0.0060 1.0000 1.0000
0.250 -0.1292 0.02602 0.01639 -0.0056 1.0000 1.0000
0.500 -0.0854 0.02725 0.01742 -0.0105 0.9887 1.0000
0.750 -0.0407 0.02849 0.01850 -0.0154 0.9754 1.0000
1.000 0.0002 0.02961 0.01947 -0.0194 0.9622 1.0000
1.250 0.0379 0.03066 0.02040 -0.0228 0.9490 1.0000
1.500 0.0747 0.03169 0.02134 -0.0259 0.9352 1.0000
1.750 0.1095 0.03272 0.02229 -0.0285 0.9215 1.0000
2.000 0.1427 0.03377 0.02329 -0.0309 0.9088 1.0000
2.250 0.1775 0.03486 0.02433 -0.0333 0.8958 1.0000
2.500 0.2147 0.03594 0.02539 -0.0360 0.8825 1.0000
2.750 0.2448 0.03690 0.02633 -0.0375 0.8685 1.0000
3.000 0.2776 0.03778 0.02722 -0.0391 0.8528 1.0000
3.250 0.3134 0.03858 0.02803 -0.0410 0.8364 1.0000
3.500 0.3496 0.03928 0.02877 -0.0427 0.8201 1.0000
3.750 0.3778 0.04002 0.02954 -0.0432 0.8049 1.0000
4.000 0.3977 0.04094 0.03050 -0.0428 0.7911 1.0000
4.250 0.4191 0.04190 0.03151 -0.0426 0.7775 1.0000
4.500 0.4413 0.04291 0.03257 -0.0426 0.7643 1.0000
4.750 0.4668 0.04386 0.03360 -0.0428 0.7509 1.0000
5.000 0.4951 0.04472 0.03457 -0.0432 0.7369 1.0000
5.250 0.5241 0.04552 0.03548 -0.0436 0.7223 1.0000
5.500 0.5552 0.04627 0.03636 -0.0441 0.7080 1.0000
5.750 0.5828 0.04703 0.03727 -0.0441 0.6924 1.0000
6.000 0.6014 0.04790 0.03825 -0.0429 0.6734 1.0000
6.250 0.7071 0.04267 0.03346 -0.0457 0.6461 1.0000
6.500 0.7578 0.03989 0.03092 -0.0443 0.6190 1.0000
6.750 0.8273 0.03609 0.02745 -0.0447 0.5945 1.0000
7.000 0.8879 0.03262 0.02421 -0.0443 0.5637 1.0000
7.250 0.9396 0.02960 0.02126 -0.0430 0.5212 1.0000
7.500 0.9612 0.02868 0.02017 -0.0391 0.4663 1.0000
7.750 0.9790 0.02896 0.01984 -0.0352 0.3947 1.0000
8.000 0.9838 0.03016 0.02076 -0.0308 0.3418 1.0000
8.250 0.9981 0.03127 0.02146 -0.0281 0.3045 1.0000
8.500 1.0227 0.03293 0.02281 -0.0273 0.2751 1.0000
8.750 1.0484 0.03499 0.02481 -0.0269 0.2526 1.0000
9.000 1.0718 0.03707 0.02695 -0.0262 0.2349 1.0000
9.250 1.0928 0.03918 0.02915 -0.0252 0.2203 1.0000
9.500 1.1109 0.04122 0.03130 -0.0239 0.2068 1.0000
9.750 1.1255 0.04313 0.03328 -0.0221 0.1931 1.0000
10.000 1.1369 0.04495 0.03515 -0.0199 0.1790 1.0000
10.250 1.1480 0.04705 0.03731 -0.0179 0.1654 1.0000
10.500 1.1618 0.04965 0.03992 -0.0164 0.1526 1.0000
10.750 1.1579 0.05246 0.04315 -0.0127 0.1452 1.0000
11.000 1.1646 0.05583 0.04663 -0.0107 0.1369 1.0000
11.250 1.1508 0.05908 0.05031 -0.0066 0.1335 1.0000
11.500 1.1425 0.06238 0.05386 -0.0034 0.1300 1.0000
11.750 1.1514 0.06627 0.05773 -0.0024 0.1241 1.0000
12.000 1.1256 0.06963 0.06138 0.0019 0.1237 1.0000
12.250 1.0998 0.07348 0.06547 0.0049 0.1236 1.0000
12.500 1.0725 0.07793 0.07013 0.0068 0.1239 1.0000
12.750 1.0462 0.08304 0.07541 0.0074 0.1244 1.0000
13.000 1.0205 0.08886 0.08135 0.0069 0.1249 1.0000
13.250 0.7761 0.13657 0.12888 -0.0276 0.1949 1.0000
13.500 0.7790 0.14271 0.13505 -0.0291 0.1965 1.0000
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