RAF 28 AIRFOIL (raf28-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 28 AIRFOIL (raf28-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.64 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf28-il-1000000-n5.txt Download as CSV file: xf-raf28-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 28 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
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0513 0.05010 0.04771 -0.0552 1.0000 0.0039
-14.500 -1.0869 0.03947 0.03679 -0.0655 1.0000 0.0039
-14.250 -1.1012 0.03553 0.03270 -0.0670 1.0000 0.0039
-14.000 -1.1145 0.03281 0.02981 -0.0654 1.0000 0.0040
-13.750 -1.1231 0.03103 0.02791 -0.0621 1.0000 0.0040
-13.500 -1.1246 0.02947 0.02623 -0.0591 1.0000 0.0041
-13.250 -1.1198 0.02804 0.02467 -0.0569 1.0000 0.0042
-13.000 -1.1130 0.02668 0.02318 -0.0547 1.0000 0.0043
-12.750 -1.1029 0.02553 0.02192 -0.0528 1.0000 0.0044
-12.500 -1.0930 0.02428 0.02053 -0.0507 1.0000 0.0045
-12.250 -1.0803 0.02326 0.01939 -0.0488 1.0000 0.0046
-12.000 -1.0669 0.02226 0.01827 -0.0470 1.0000 0.0047
-11.750 -1.0521 0.02137 0.01726 -0.0453 1.0000 0.0048
-11.500 -1.0372 0.02044 0.01621 -0.0435 1.0000 0.0049
-11.250 -1.0213 0.01959 0.01524 -0.0418 1.0000 0.0050
-11.000 -1.0041 0.01888 0.01442 -0.0403 1.0000 0.0051
-10.750 -0.9886 0.01793 0.01336 -0.0385 1.0000 0.0054
-10.500 -0.9678 0.01714 0.01247 -0.0376 0.9997 0.0057
-10.250 -0.9383 0.01640 0.01165 -0.0386 0.9982 0.0061
-10.000 -0.9079 0.01572 0.01089 -0.0397 0.9964 0.0064
-9.750 -0.8768 0.01509 0.01017 -0.0409 0.9944 0.0068
-9.500 -0.8482 0.01453 0.00951 -0.0414 0.9918 0.0072
-9.250 -0.8186 0.01396 0.00886 -0.0422 0.9889 0.0076
-9.000 -0.7877 0.01337 0.00822 -0.0433 0.9863 0.0085
-8.750 -0.7602 0.01289 0.00770 -0.0435 0.9819 0.0092
-8.500 -0.7307 0.01244 0.00719 -0.0441 0.9772 0.0100
-8.250 -0.7029 0.01201 0.00671 -0.0443 0.9708 0.0109
-7.750 -0.6380 0.01134 0.00603 -0.0467 0.9577 0.0140
-7.500 -0.6000 0.01102 0.00571 -0.0491 0.9499 0.0157
-7.250 -0.5600 0.01086 0.00556 -0.0519 0.9366 0.0176
-7.000 -0.5210 0.01066 0.00529 -0.0545 0.9142 0.0192
-6.750 -0.4899 0.01058 0.00508 -0.0552 0.8858 0.0201
-6.500 -0.4636 0.01052 0.00490 -0.0549 0.8647 0.0206
-6.000 -0.4141 0.01004 0.00423 -0.0537 0.8393 0.0224
-5.750 -0.3890 0.00980 0.00393 -0.0532 0.8304 0.0234
-5.500 -0.3635 0.00963 0.00370 -0.0527 0.8224 0.0244
-5.250 -0.3376 0.00946 0.00348 -0.0523 0.8152 0.0253
-5.000 -0.3118 0.00929 0.00325 -0.0519 0.8078 0.0260
-4.750 -0.2857 0.00911 0.00303 -0.0515 0.8008 0.0267
-4.500 -0.2598 0.00893 0.00278 -0.0511 0.7935 0.0272
-4.250 -0.2336 0.00876 0.00255 -0.0507 0.7869 0.0276
-4.000 -0.2073 0.00860 0.00235 -0.0504 0.7799 0.0280
-3.750 -0.1809 0.00847 0.00218 -0.0501 0.7733 0.0287
-3.500 -0.1543 0.00834 0.00201 -0.0497 0.7658 0.0292
-3.250 -0.1277 0.00823 0.00186 -0.0494 0.7582 0.0296
-3.000 -0.1011 0.00813 0.00172 -0.0491 0.7495 0.0299
-2.750 -0.0745 0.00800 0.00155 -0.0488 0.7407 0.0316
-2.500 -0.0480 0.00791 0.00142 -0.0485 0.7301 0.0338
-2.250 -0.0216 0.00783 0.00131 -0.0481 0.7170 0.0363
-2.000 0.0046 0.00776 0.00121 -0.0477 0.7019 0.0393
-1.750 0.0301 0.00762 0.00110 -0.0472 0.6854 0.0647
-1.500 0.0556 0.00750 0.00103 -0.0467 0.6690 0.0912
-1.250 0.0812 0.00741 0.00096 -0.0463 0.6542 0.1154
-1.000 0.1065 0.00726 0.00090 -0.0458 0.6403 0.1562
-0.750 0.1313 0.00705 0.00085 -0.0453 0.6290 0.2225
-0.500 0.1567 0.00690 0.00083 -0.0448 0.6182 0.2736
-0.250 0.1822 0.00677 0.00082 -0.0444 0.6070 0.3211
0.000 0.2065 0.00652 0.00081 -0.0438 0.5962 0.4046
0.250 0.2306 0.00633 0.00082 -0.0431 0.5822 0.4838
0.500 0.2551 0.00618 0.00083 -0.0424 0.5692 0.5492
0.750 0.2762 0.00585 0.00087 -0.0410 0.5569 0.6766
1.000 0.2996 0.00571 0.00091 -0.0400 0.5449 0.7439
1.500 0.3472 0.00562 0.00099 -0.0381 0.5108 0.8292
1.750 0.3720 0.00557 0.00106 -0.0373 0.4941 0.8794
2.000 0.4045 0.00572 0.00118 -0.0383 0.4584 0.9261
2.250 0.4441 0.00592 0.00130 -0.0410 0.4299 0.9500
2.500 0.4795 0.00614 0.00140 -0.0428 0.4009 0.9615
2.750 0.5150 0.00636 0.00151 -0.0446 0.3735 0.9681
3.250 0.5771 0.00690 0.00180 -0.0463 0.3075 0.9825
3.500 0.6094 0.00746 0.00206 -0.0476 0.2384 0.9890
3.750 0.6438 0.00786 0.00229 -0.0494 0.1970 0.9944
4.250 0.7126 0.00876 0.00278 -0.0530 0.1119 1.0000
4.500 0.7345 0.00899 0.00297 -0.0518 0.0982 1.0000
4.750 0.7537 0.00945 0.00323 -0.0502 0.0597 1.0000
5.000 0.7731 0.00988 0.00354 -0.0486 0.0353 1.0000
5.250 0.7954 0.01011 0.00377 -0.0475 0.0314 1.0000
5.500 0.8173 0.01036 0.00402 -0.0464 0.0280 1.0000
5.750 0.8393 0.01061 0.00427 -0.0452 0.0249 1.0000
6.000 0.8619 0.01081 0.00449 -0.0442 0.0232 1.0000
6.250 0.8838 0.01107 0.00475 -0.0431 0.0202 1.0000
6.500 0.9051 0.01138 0.00506 -0.0419 0.0167 1.0000
6.750 0.9268 0.01166 0.00534 -0.0407 0.0146 1.0000
7.000 0.9478 0.01199 0.00565 -0.0395 0.0124 1.0000
7.250 0.9691 0.01231 0.00599 -0.0383 0.0112 1.0000
7.500 0.9904 0.01263 0.00634 -0.0371 0.0104 1.0000
7.750 1.0113 0.01297 0.00670 -0.0359 0.0096 1.0000
8.000 1.0316 0.01336 0.00711 -0.0345 0.0086 1.0000
8.250 1.0514 0.01379 0.00757 -0.0331 0.0079 1.0000
8.500 1.0719 0.01414 0.00796 -0.0319 0.0075 1.0000
8.750 1.0919 0.01454 0.00839 -0.0306 0.0070 1.0000
9.000 1.1113 0.01496 0.00885 -0.0292 0.0067 1.0000
9.250 1.1303 0.01541 0.00933 -0.0277 0.0063 1.0000
9.500 1.1485 0.01591 0.00986 -0.0262 0.0059 1.0000
9.750 1.1641 0.01659 0.01062 -0.0242 0.0055 1.0000
10.000 1.1818 0.01708 0.01117 -0.0226 0.0054 1.0000
10.250 1.1991 0.01758 0.01172 -0.0210 0.0053 1.0000
10.500 1.2152 0.01814 0.01234 -0.0192 0.0050 1.0000
10.750 1.2301 0.01872 0.01298 -0.0172 0.0049 1.0000
11.000 1.2421 0.01931 0.01363 -0.0147 0.0047 1.0000
11.250 1.2544 0.01987 0.01424 -0.0123 0.0045 1.0000
11.500 1.2670 0.02046 0.01487 -0.0101 0.0043 1.0000
11.750 1.2774 0.02120 0.01569 -0.0077 0.0042 1.0000
12.000 1.2885 0.02195 0.01650 -0.0056 0.0040 1.0000
12.250 1.2941 0.02309 0.01773 -0.0029 0.0038 1.0000
12.500 1.3011 0.02419 0.01891 -0.0006 0.0037 1.0000
12.750 1.3087 0.02531 0.02013 0.0013 0.0037 1.0000
13.000 1.3134 0.02671 0.02164 0.0033 0.0037 1.0000
13.250 1.3235 0.02776 0.02278 0.0046 0.0036 1.0000
13.500 1.3292 0.02925 0.02437 0.0060 0.0035 1.0000
13.750 1.3327 0.03101 0.02624 0.0073 0.0035 1.0000
14.000 1.3387 0.03261 0.02793 0.0082 0.0034 1.0000
14.250 1.3409 0.03465 0.03009 0.0091 0.0034 1.0000
14.500 1.3393 0.03718 0.03275 0.0099 0.0033 1.0000
14.750 1.3430 0.03927 0.03493 0.0102 0.0032 1.0000
15.000 1.3391 0.04231 0.03811 0.0103 0.0032 1.0000
15.250 1.3397 0.04497 0.04088 0.0102 0.0032 1.0000
15.500 1.3358 0.04829 0.04433 0.0097 0.0031 1.0000
15.750 1.3249 0.05263 0.04882 0.0088 0.0031 1.0000
16.000 1.3228 0.05600 0.05229 0.0079 0.0031 1.0000
16.250 1.3177 0.05991 0.05631 0.0067 0.0030 1.0000
16.500 1.3087 0.06452 0.06105 0.0050 0.0029 1.0000
16.750 1.2876 0.07120 0.06790 0.0023 0.0030 1.0000
17.000 1.2758 0.07671 0.07354 -0.0001 0.0030 1.0000
17.250 1.2649 0.08223 0.07916 -0.0026 0.0029 1.0000
17.500 1.2398 0.09041 0.08751 -0.0064 0.0030 1.0000
17.750 1.2175 0.09842 0.09566 -0.0104 0.0030 1.0000
18.000 1.1991 0.10598 0.10333 -0.0141 0.0029 1.0000
18.250 1.1724 0.11546 0.11296 -0.0189 0.0030 1.0000
18.500 1.1352 0.12752 0.12520 -0.0250 0.0031 1.0000
18.750 1.1136 0.13667 0.13445 -0.0298 0.0030 1.0000
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