RAF 28 AIRFOIL (raf28-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 28 AIRFOIL (raf28-il) Reynolds number: 100,000 Max Cl/Cd: 52.56 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf28-il-100000.txt Download as CSV file: xf-raf28-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4721 0.10845 0.10321 -0.0201 1.0000 0.1160
-9.750 -0.4803 0.10529 0.10011 -0.0230 1.0000 0.1210
-9.500 -0.5185 0.10253 0.09757 -0.0313 1.0000 0.1228
-9.250 -0.4766 0.09753 0.09244 -0.0243 1.0000 0.1268
-9.000 -0.4729 0.09440 0.08934 -0.0245 1.0000 0.1321
-8.750 -0.5061 0.09109 0.08621 -0.0309 1.0000 0.1366
-8.500 -0.4957 0.08671 0.08185 -0.0293 1.0000 0.1395
-8.250 -0.4834 0.08417 0.07930 -0.0273 1.0000 0.1473
-8.000 -0.5170 0.08034 0.07562 -0.0321 1.0000 0.1505
-7.750 -0.5024 0.07726 0.07258 -0.0286 1.0000 0.1567
-7.500 -0.5201 0.07356 0.06890 -0.0318 1.0000 0.1645
-7.250 -0.5137 0.07025 0.06565 -0.0298 1.0000 0.1708
-7.000 -0.4424 0.05658 0.05234 -0.0280 1.0000 0.1866
-6.750 -0.5155 0.06388 0.05930 -0.0289 1.0000 0.1873
-6.500 -0.5204 0.06057 0.05597 -0.0287 1.0000 0.1987
-6.250 -0.5482 0.04130 0.03503 -0.0339 1.0000 0.0909
-6.000 -0.5462 0.03683 0.02946 -0.0301 1.0000 0.0808
-5.750 -0.5344 0.03423 0.02652 -0.0277 1.0000 0.0803
-5.500 -0.5234 0.03116 0.02316 -0.0257 1.0000 0.0818
-5.250 -0.5088 0.02901 0.02078 -0.0238 1.0000 0.0831
-5.000 -0.4922 0.02709 0.01853 -0.0219 1.0000 0.0834
-4.750 -0.4742 0.02551 0.01673 -0.0202 1.0000 0.0847
-4.500 -0.4560 0.02443 0.01549 -0.0187 1.0000 0.0886
-4.250 -0.4363 0.02330 0.01410 -0.0172 1.0000 0.0914
-4.000 -0.4155 0.02227 0.01284 -0.0158 1.0000 0.0934
-3.750 -0.3947 0.02104 0.01157 -0.0146 1.0000 0.0965
-3.500 -0.3754 0.02028 0.01086 -0.0134 1.0000 0.1022
-3.250 -0.3561 0.01964 0.01012 -0.0120 1.0000 0.1094
-3.000 -0.3381 0.01887 0.00950 -0.0106 1.0000 0.1177
-2.750 -0.3207 0.01818 0.00890 -0.0090 1.0000 0.1320
-2.500 -0.2963 0.01663 0.00824 -0.0091 0.9969 0.2472
-2.250 -0.2634 0.01539 0.00838 -0.0106 0.9891 0.5417
-1.750 -0.1133 0.01500 0.00887 -0.0271 0.9879 1.0000
-1.500 -0.0647 0.01521 0.00881 -0.0321 0.9778 1.0000
-1.250 -0.0156 0.01540 0.00875 -0.0370 0.9683 1.0000
-1.000 0.0322 0.01551 0.00869 -0.0415 0.9583 1.0000
-0.750 0.0751 0.01558 0.00861 -0.0450 0.9470 1.0000
-0.500 0.1199 0.01563 0.00853 -0.0487 0.9366 1.0000
-0.250 0.1726 0.01559 0.00839 -0.0537 0.9291 1.0000
0.000 0.2146 0.01555 0.00829 -0.0567 0.9178 1.0000
0.250 0.2607 0.01547 0.00815 -0.0604 0.9081 1.0000
0.500 0.3118 0.01524 0.00790 -0.0648 0.9002 1.0000
0.750 0.3486 0.01518 0.00782 -0.0664 0.8879 1.0000
1.000 0.3846 0.01512 0.00775 -0.0679 0.8756 1.0000
1.250 0.4192 0.01510 0.00772 -0.0689 0.8634 1.0000
1.500 0.4520 0.01509 0.00772 -0.0695 0.8510 1.0000
1.750 0.4830 0.01512 0.00774 -0.0697 0.8387 1.0000
2.000 0.5113 0.01520 0.00783 -0.0693 0.8257 1.0000
2.250 0.5354 0.01538 0.00803 -0.0682 0.8114 1.0000
2.500 0.5588 0.01557 0.00824 -0.0670 0.7971 1.0000
2.750 0.5819 0.01575 0.00844 -0.0656 0.7824 1.0000
3.000 0.6055 0.01583 0.00853 -0.0641 0.7669 1.0000
3.250 0.6256 0.01592 0.00868 -0.0621 0.7483 1.0000
3.500 0.6474 0.01588 0.00866 -0.0601 0.7294 1.0000
3.750 0.6711 0.01575 0.00853 -0.0583 0.7106 1.0000
4.000 0.6953 0.01567 0.00848 -0.0567 0.6932 1.0000
4.250 0.7170 0.01576 0.00865 -0.0550 0.6752 1.0000
4.500 0.7396 0.01581 0.00874 -0.0534 0.6560 1.0000
4.750 0.7619 0.01572 0.00863 -0.0513 0.6312 1.0000
5.000 0.7830 0.01570 0.00860 -0.0491 0.6032 1.0000
5.250 0.8028 0.01576 0.00867 -0.0468 0.5737 1.0000
5.500 0.8204 0.01582 0.00875 -0.0442 0.5371 1.0000
5.750 0.8367 0.01592 0.00881 -0.0414 0.4920 1.0000
6.000 0.8508 0.01621 0.00898 -0.0382 0.4326 1.0000
6.250 0.8580 0.01703 0.00931 -0.0342 0.3206 1.0000
6.500 0.8505 0.01961 0.01059 -0.0287 0.1563 1.0000
6.750 0.8538 0.02171 0.01220 -0.0248 0.1070 1.0000
7.000 0.8652 0.02312 0.01351 -0.0220 0.0908 1.0000
7.250 0.8795 0.02446 0.01482 -0.0196 0.0813 1.0000
7.500 0.8953 0.02591 0.01615 -0.0178 0.0735 1.0000
7.750 0.9166 0.02736 0.01771 -0.0164 0.0686 1.0000
8.000 0.9401 0.02914 0.01942 -0.0156 0.0647 1.0000
8.250 0.9655 0.03138 0.02177 -0.0151 0.0608 1.0000
8.500 0.9895 0.03345 0.02408 -0.0143 0.0581 1.0000
8.750 1.0126 0.03607 0.02698 -0.0133 0.0568 1.0000
9.000 1.0315 0.03898 0.03028 -0.0118 0.0565 1.0000
9.250 1.0459 0.04186 0.03353 -0.0099 0.0556 1.0000
9.500 1.0602 0.04452 0.03636 -0.0084 0.0539 1.0000
9.750 1.0695 0.04773 0.03987 -0.0064 0.0532 1.0000
10.000 1.0617 0.05180 0.04467 -0.0022 0.0551 1.0000
10.250 1.0500 0.05637 0.04978 0.0015 0.0573 1.0000
10.500 1.0393 0.06061 0.05434 0.0045 0.0590 1.0000
10.750 1.0287 0.06474 0.05868 0.0070 0.0606 1.0000
11.000 1.0372 0.06977 0.06381 0.0077 0.0639 1.0000
11.250 0.9912 0.07239 0.06679 0.0121 0.0649 1.0000
11.500 0.9469 0.07753 0.07220 0.0119 0.0660 1.0000
11.750 0.9074 0.08434 0.07919 0.0087 0.0670 1.0000
12.000 0.8615 0.09456 0.08950 0.0013 0.0688 1.0000
12.250 0.8357 0.10472 0.09966 -0.0047 0.0724 1.0000
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Polar data table (+)
Polar graphs
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