RAF 28 AIRFOIL (raf28-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 28 AIRFOIL (raf28-il) Reynolds number: 50,000 Max Cl/Cd: 35.57 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf28-il-50000.txt Download as CSV file: xf-raf28-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4401 0.09599 0.08891 -0.0087 1.0000 0.3306
-8.000 -0.4485 0.09395 0.08698 -0.0083 1.0000 0.3436
-7.750 -0.4535 0.09172 0.08483 -0.0073 1.0000 0.3576
-7.500 -0.4346 0.08735 0.08045 -0.0060 1.0000 0.3745
-7.000 -0.4241 0.08121 0.07441 -0.0034 1.0000 0.4055
-6.500 -0.5415 0.05745 0.05025 -0.0349 1.0000 0.1665
-6.250 -0.5349 0.05196 0.04451 -0.0345 1.0000 0.1537
-6.000 -0.5262 0.04792 0.04017 -0.0335 1.0000 0.1480
-5.750 -0.5176 0.04434 0.03625 -0.0321 1.0000 0.1466
-5.500 -0.5073 0.04103 0.03254 -0.0305 1.0000 0.1460
-5.250 -0.4947 0.03788 0.02893 -0.0288 1.0000 0.1444
-5.000 -0.4796 0.03509 0.02566 -0.0271 1.0000 0.1436
-4.750 -0.4624 0.03274 0.02287 -0.0254 1.0000 0.1446
-4.500 -0.4445 0.03088 0.02055 -0.0237 1.0000 0.1497
-4.250 -0.4253 0.02906 0.01852 -0.0223 1.0000 0.1553
-4.000 -0.4043 0.02750 0.01676 -0.0209 1.0000 0.1610
-3.750 -0.3821 0.02598 0.01503 -0.0196 1.0000 0.1687
-3.500 -0.3599 0.02473 0.01370 -0.0183 1.0000 0.1820
-3.250 -0.3378 0.02358 0.01267 -0.0172 1.0000 0.2082
-3.000 -0.3139 0.02208 0.01156 -0.0162 1.0000 0.2683
-2.750 -0.3028 0.01954 0.01078 -0.0125 1.0000 0.5112
-2.500 -0.1347 0.01898 0.01093 -0.0307 1.0000 1.0000
-2.250 -0.1490 0.01867 0.01042 -0.0258 1.0000 1.0000
-2.000 -0.1482 0.01862 0.01009 -0.0227 1.0000 1.0000
-1.750 -0.1419 0.01870 0.00988 -0.0202 1.0000 1.0000
-1.500 -0.1328 0.01886 0.00979 -0.0180 1.0000 1.0000
-1.250 -0.1219 0.01909 0.00978 -0.0161 1.0000 1.0000
-1.000 -0.1098 0.01936 0.00984 -0.0145 1.0000 1.0000
-0.750 -0.0967 0.01969 0.00997 -0.0130 1.0000 1.0000
-0.500 -0.0831 0.02006 0.01015 -0.0118 1.0000 1.0000
-0.250 -0.0690 0.02048 0.01040 -0.0107 1.0000 1.0000
0.000 -0.0544 0.02094 0.01072 -0.0097 1.0000 1.0000
0.250 -0.0396 0.02145 0.01109 -0.0088 1.0000 1.0000
0.500 -0.0246 0.02199 0.01151 -0.0080 1.0000 1.0000
0.750 -0.0093 0.02258 0.01198 -0.0074 1.0000 1.0000
1.000 0.0410 0.02377 0.01307 -0.0135 0.9858 1.0000
1.250 0.0882 0.02486 0.01408 -0.0187 0.9720 1.0000
1.500 0.1327 0.02585 0.01501 -0.0232 0.9580 1.0000
1.750 0.1745 0.02676 0.01590 -0.0272 0.9438 1.0000
2.000 0.2143 0.02762 0.01677 -0.0307 0.9297 1.0000
2.250 0.2529 0.02846 0.01763 -0.0338 0.9154 1.0000
2.500 0.2897 0.02927 0.01848 -0.0364 0.9010 1.0000
2.750 0.3254 0.03008 0.01936 -0.0388 0.8865 1.0000
3.000 0.3598 0.03089 0.02025 -0.0408 0.8720 1.0000
3.250 0.3945 0.03169 0.02114 -0.0428 0.8572 1.0000
3.500 0.4292 0.03247 0.02206 -0.0446 0.8421 1.0000
3.750 0.4656 0.03319 0.02292 -0.0464 0.8267 1.0000
4.000 0.5055 0.03380 0.02371 -0.0485 0.8107 1.0000
4.250 0.5273 0.03464 0.02470 -0.0479 0.7927 1.0000
4.500 0.5587 0.03522 0.02546 -0.0484 0.7739 1.0000
4.750 0.6118 0.03501 0.02557 -0.0510 0.7543 1.0000
5.000 0.6534 0.03446 0.02532 -0.0509 0.7287 1.0000
5.250 0.7051 0.03293 0.02413 -0.0507 0.7017 1.0000
5.500 0.7573 0.03125 0.02283 -0.0505 0.6782 1.0000
5.750 0.7922 0.03024 0.02212 -0.0484 0.6512 1.0000
6.000 0.8343 0.02732 0.01938 -0.0444 0.6066 1.0000
6.250 0.8574 0.02526 0.01733 -0.0388 0.5484 1.0000
6.500 0.8680 0.02440 0.01641 -0.0330 0.4816 1.0000
6.750 0.8666 0.02448 0.01592 -0.0259 0.3700 1.0000
7.000 0.8541 0.02719 0.01718 -0.0191 0.2351 1.0000
7.250 0.8621 0.03016 0.01941 -0.0159 0.1742 1.0000
7.500 0.8883 0.03267 0.02166 -0.0150 0.1462 1.0000
7.750 0.9204 0.03536 0.02405 -0.0152 0.1282 1.0000
8.000 0.9485 0.03789 0.02698 -0.0144 0.1190 1.0000
8.250 0.9745 0.04100 0.03023 -0.0139 0.1122 1.0000
8.500 0.9915 0.04369 0.03337 -0.0121 0.1067 1.0000
8.750 1.0109 0.04690 0.03681 -0.0110 0.1033 1.0000
9.000 1.0266 0.05060 0.04083 -0.0095 0.1021 1.0000
9.250 1.0369 0.05454 0.04514 -0.0076 0.1015 1.0000
9.500 1.0433 0.05894 0.04984 -0.0059 0.1006 1.0000
9.750 1.0428 0.06281 0.05413 -0.0034 0.1004 1.0000
10.000 1.0374 0.06671 0.05841 -0.0010 0.1003 1.0000
10.250 1.0329 0.07110 0.06308 0.0010 0.1005 1.0000
10.500 0.9617 0.07468 0.06735 0.0062 0.1076 1.0000
10.750 0.9337 0.07944 0.07224 0.0070 0.1096 1.0000
11.000 0.9116 0.08492 0.07780 0.0061 0.1117 1.0000
11.250 0.8969 0.09071 0.08363 0.0046 0.1132 1.0000
11.500 0.8953 0.09644 0.08937 0.0036 0.1143 1.0000
11.750 0.8347 0.11032 0.10326 -0.0073 0.1280 1.0000
12.000 0.7272 0.14391 0.13648 -0.0396 0.2832 1.0000
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Polar data table (+)
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