RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 100 AIRFOIL (rae100-il) Reynolds number: 50,000 Max Cl/Cd: 24.63 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae100-il-50000.txt Download as CSV file: xf-rae100-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 100 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.7480 0.07854 0.07140 -0.0130 1.0000 0.1540
-9.000 -0.7540 0.07297 0.06580 -0.0141 1.0000 0.1520
-8.750 -0.7688 0.06681 0.05954 -0.0156 1.0000 0.1491
-8.500 -0.7907 0.05989 0.05230 -0.0168 1.0000 0.1454
-8.250 -0.8027 0.05377 0.04567 -0.0168 1.0000 0.1435
-8.000 -0.7960 0.04974 0.04134 -0.0160 1.0000 0.1459
-7.750 -0.7890 0.04597 0.03715 -0.0149 1.0000 0.1505
-7.500 -0.7829 0.04203 0.03243 -0.0135 1.0000 0.1547
-7.250 -0.7619 0.03940 0.02990 -0.0126 1.0000 0.1622
-7.000 -0.7466 0.03655 0.02658 -0.0113 1.0000 0.1718
-6.750 -0.7274 0.03420 0.02391 -0.0100 1.0000 0.1832
-6.500 -0.7071 0.03216 0.02172 -0.0088 1.0000 0.1984
-6.250 -0.6854 0.03023 0.01983 -0.0077 1.0000 0.2161
-6.000 -0.6640 0.02865 0.01828 -0.0063 1.0000 0.2393
-5.750 -0.6430 0.02713 0.01687 -0.0049 1.0000 0.2672
-5.500 -0.6227 0.02577 0.01557 -0.0033 1.0000 0.3021
-5.250 -0.6026 0.02464 0.01470 -0.0014 1.0000 0.3421
-5.000 -0.5833 0.02369 0.01396 0.0008 1.0000 0.3879
-4.750 -0.5643 0.02292 0.01342 0.0033 1.0000 0.4361
-4.500 -0.5454 0.02229 0.01300 0.0059 1.0000 0.4850
-4.250 -0.5267 0.02179 0.01268 0.0088 1.0000 0.5327
-4.000 -0.5078 0.02139 0.01244 0.0118 1.0000 0.5782
-3.750 -0.4890 0.02106 0.01226 0.0151 1.0000 0.6218
-3.500 -0.4704 0.02076 0.01205 0.0184 1.0000 0.6643
-3.250 -0.4525 0.02046 0.01181 0.0219 1.0000 0.7068
-3.000 -0.4316 0.02033 0.01173 0.0253 1.0000 0.7461
-2.750 -0.4101 0.02016 0.01158 0.0284 1.0000 0.7871
-2.500 -0.3792 0.02020 0.01159 0.0301 1.0000 0.8279
-2.250 -0.3287 0.02042 0.01165 0.0282 1.0000 0.8692
-2.000 -0.2530 0.02067 0.01163 0.0208 1.0000 0.9105
-1.750 -0.1451 0.02050 0.01111 0.0063 1.0000 0.9467
-1.500 -0.0553 0.01970 0.01008 -0.0065 1.0000 0.9822
-1.250 0.0002 0.01870 0.00900 -0.0141 1.0000 1.0000
-1.000 0.0066 0.01814 0.00848 -0.0127 1.0000 1.0000
-0.750 0.0107 0.01768 0.00806 -0.0107 1.0000 1.0000
-0.500 0.0112 0.01732 0.00776 -0.0079 1.0000 1.0000
-0.250 0.0076 0.01708 0.00757 -0.0043 1.0000 1.0000
0.000 0.0000 0.01700 0.00752 0.0000 1.0000 1.0000
0.250 -0.0076 0.01708 0.00757 0.0043 1.0000 1.0000
0.500 -0.0113 0.01732 0.00776 0.0079 1.0000 1.0000
0.750 -0.0107 0.01768 0.00806 0.0107 1.0000 1.0000
1.000 -0.0066 0.01814 0.00847 0.0127 1.0000 1.0000
1.250 -0.0001 0.01870 0.00900 0.0141 1.0000 1.0000
1.500 0.0552 0.01970 0.01008 0.0065 0.9823 1.0000
1.750 0.1448 0.02050 0.01110 -0.0062 0.9468 1.0000
2.000 0.2523 0.02068 0.01163 -0.0207 0.9106 1.0000
2.250 0.3286 0.02043 0.01165 -0.0282 0.8693 1.0000
2.500 0.3793 0.02020 0.01158 -0.0301 0.8279 1.0000
2.750 0.4102 0.02016 0.01158 -0.0284 0.7871 1.0000
3.000 0.4317 0.02033 0.01173 -0.0253 0.7461 1.0000
3.250 0.4526 0.02046 0.01181 -0.0219 0.7068 1.0000
3.500 0.4706 0.02076 0.01205 -0.0185 0.6643 1.0000
3.750 0.4891 0.02106 0.01226 -0.0151 0.6217 1.0000
4.000 0.5079 0.02139 0.01244 -0.0119 0.5782 1.0000
4.250 0.5268 0.02179 0.01268 -0.0088 0.5327 1.0000
4.500 0.5455 0.02229 0.01300 -0.0059 0.4849 1.0000
4.750 0.5644 0.02292 0.01342 -0.0033 0.4361 1.0000
5.000 0.5834 0.02369 0.01396 -0.0008 0.3877 1.0000
5.250 0.6027 0.02463 0.01470 0.0013 0.3421 1.0000
5.500 0.6228 0.02577 0.01557 0.0032 0.3021 1.0000
5.750 0.6430 0.02713 0.01687 0.0049 0.2672 1.0000
6.000 0.6641 0.02865 0.01829 0.0063 0.2393 1.0000
6.250 0.6854 0.03023 0.01983 0.0077 0.2161 1.0000
6.500 0.7072 0.03216 0.02171 0.0088 0.1985 1.0000
6.750 0.7273 0.03420 0.02391 0.0100 0.1832 1.0000
7.000 0.7466 0.03654 0.02657 0.0113 0.1717 1.0000
7.250 0.7618 0.03940 0.02989 0.0126 0.1623 1.0000
7.500 0.7827 0.04202 0.03242 0.0135 0.1547 1.0000
7.750 0.7889 0.04596 0.03713 0.0149 0.1505 1.0000
8.000 0.7960 0.04970 0.04130 0.0160 0.1459 1.0000
8.250 0.8028 0.05372 0.04562 0.0168 0.1435 1.0000
8.500 0.7905 0.05988 0.05229 0.0168 0.1455 1.0000
8.750 0.7690 0.06676 0.05948 0.0156 0.1491 1.0000
9.000 0.7540 0.07293 0.06576 0.0142 0.1520 1.0000
9.250 0.7480 0.07850 0.07136 0.0130 0.1539 1.0000
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Polar data table (+)
Polar graphs
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