RAE 102 AIRFOIL (rae102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 102 AIRFOIL (rae102-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.29 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae102-il-1000000-n5.txt Download as CSV file: xf-rae102-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 102 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9447 0.11912 0.11722 0.0069 1.0000 0.0043
-16.250 -0.9911 0.10440 0.10237 -0.0005 1.0000 0.0041
-16.000 -1.0566 0.08557 0.08333 -0.0106 1.0000 0.0041
-15.750 -1.0905 0.07392 0.07151 -0.0177 1.0000 0.0040
-15.500 -1.1141 0.06530 0.06274 -0.0232 1.0000 0.0040
-15.250 -1.1354 0.05791 0.05519 -0.0278 1.0000 0.0040
-15.000 -1.1564 0.05122 0.04832 -0.0316 1.0000 0.0040
-14.750 -1.1732 0.04574 0.04266 -0.0342 1.0000 0.0040
-14.500 -1.1795 0.04204 0.03883 -0.0355 1.0000 0.0040
-14.250 -1.1836 0.03891 0.03556 -0.0362 1.0000 0.0041
-14.000 -1.1907 0.03579 0.03228 -0.0363 1.0000 0.0041
-13.750 -1.1917 0.03352 0.02988 -0.0357 1.0000 0.0041
-13.500 -1.2014 0.03078 0.02695 -0.0341 1.0000 0.0042
-13.250 -1.2051 0.02879 0.02480 -0.0319 1.0000 0.0042
-13.000 -1.2075 0.02707 0.02293 -0.0291 1.0000 0.0043
-12.750 -1.2071 0.02568 0.02141 -0.0260 1.0000 0.0044
-12.500 -1.2013 0.02467 0.02030 -0.0233 1.0000 0.0045
-12.250 -1.1913 0.02363 0.01916 -0.0211 1.0000 0.0046
-12.000 -1.1776 0.02276 0.01819 -0.0195 1.0000 0.0047
-11.750 -1.1637 0.02182 0.01714 -0.0179 1.0000 0.0048
-11.500 -1.1476 0.02104 0.01627 -0.0165 1.0000 0.0049
-11.250 -1.1302 0.02032 0.01548 -0.0152 1.0000 0.0050
-11.000 -1.1128 0.01956 0.01463 -0.0139 1.0000 0.0052
-10.750 -1.0941 0.01889 0.01389 -0.0127 1.0000 0.0053
-10.500 -1.0754 0.01821 0.01312 -0.0115 1.0000 0.0055
-10.250 -1.0556 0.01762 0.01246 -0.0104 1.0000 0.0058
-10.000 -1.0357 0.01703 0.01178 -0.0093 1.0000 0.0059
-9.750 -1.0151 0.01650 0.01119 -0.0083 1.0000 0.0061
-9.500 -0.9940 0.01603 0.01065 -0.0073 1.0000 0.0063
-9.250 -0.9753 0.01528 0.00982 -0.0059 1.0000 0.0065
-9.000 -0.9558 0.01462 0.00909 -0.0046 1.0000 0.0068
-8.750 -0.9350 0.01413 0.00855 -0.0035 1.0000 0.0071
-8.500 -0.9137 0.01368 0.00808 -0.0024 1.0000 0.0075
-8.250 -0.8921 0.01328 0.00763 -0.0014 1.0000 0.0079
-8.000 -0.8704 0.01289 0.00719 -0.0004 1.0000 0.0082
-7.750 -0.8487 0.01251 0.00677 0.0007 1.0000 0.0086
-7.500 -0.8267 0.01217 0.00639 0.0017 1.0000 0.0090
-7.250 -0.8051 0.01180 0.00599 0.0028 1.0000 0.0094
-7.000 -0.7740 0.01134 0.00549 0.0018 0.9972 0.0104
-6.750 -0.7435 0.01099 0.00514 0.0009 0.9930 0.0113
-6.500 -0.7132 0.01070 0.00482 0.0002 0.9879 0.0124
-6.000 -0.6496 0.01003 0.00413 -0.0020 0.9773 0.0153
-5.750 -0.6154 0.00974 0.00383 -0.0035 0.9708 0.0171
-5.500 -0.5816 0.00947 0.00354 -0.0050 0.9609 0.0195
-5.250 -0.5473 0.00918 0.00326 -0.0066 0.9477 0.0233
-5.000 -0.5155 0.00897 0.00301 -0.0075 0.9293 0.0272
-4.750 -0.4881 0.00877 0.00278 -0.0075 0.9057 0.0324
-4.500 -0.4627 0.00861 0.00257 -0.0070 0.8815 0.0404
-4.250 -0.4377 0.00846 0.00238 -0.0064 0.8580 0.0498
-4.000 -0.4126 0.00831 0.00219 -0.0058 0.8377 0.0622
-3.750 -0.3875 0.00811 0.00201 -0.0053 0.8189 0.0823
-3.500 -0.3625 0.00790 0.00184 -0.0048 0.8008 0.1081
-3.250 -0.3378 0.00764 0.00166 -0.0043 0.7838 0.1459
-3.000 -0.3131 0.00737 0.00149 -0.0038 0.7679 0.1911
-2.750 -0.2888 0.00702 0.00132 -0.0032 0.7533 0.2518
-2.500 -0.2646 0.00664 0.00115 -0.0027 0.7399 0.3222
-2.250 -0.2406 0.00624 0.00101 -0.0021 0.7272 0.4013
-2.000 -0.2151 0.00603 0.00094 -0.0017 0.7152 0.4555
-1.750 -0.1887 0.00592 0.00088 -0.0014 0.7034 0.4878
-1.500 -0.1621 0.00584 0.00084 -0.0012 0.6915 0.5127
-1.000 -0.1082 0.00573 0.00078 -0.0008 0.6694 0.5535
-0.750 -0.0811 0.00569 0.00076 -0.0006 0.6589 0.5716
-0.500 -0.0541 0.00566 0.00075 -0.0004 0.6473 0.5887
-0.250 -0.0270 0.00565 0.00074 -0.0002 0.6345 0.6051
0.000 0.0000 0.00564 0.00073 0.0000 0.6202 0.6203
0.250 0.0270 0.00565 0.00074 0.0002 0.6049 0.6344
0.500 0.0541 0.00566 0.00075 0.0004 0.5887 0.6473
0.750 0.0811 0.00569 0.00076 0.0006 0.5715 0.6590
1.000 0.1082 0.00573 0.00078 0.0008 0.5535 0.6695
1.500 0.1621 0.00584 0.00084 0.0012 0.5123 0.6914
1.750 0.1888 0.00592 0.00088 0.0014 0.4874 0.7033
2.000 0.2152 0.00602 0.00094 0.0017 0.4572 0.7152
2.250 0.2407 0.00623 0.00101 0.0021 0.4049 0.7272
2.500 0.2645 0.00665 0.00116 0.0027 0.3207 0.7399
2.750 0.2888 0.00702 0.00132 0.0032 0.2514 0.7533
3.000 0.3131 0.00737 0.00149 0.0038 0.1900 0.7678
3.250 0.3380 0.00764 0.00166 0.0043 0.1470 0.7836
3.500 0.3626 0.00790 0.00184 0.0048 0.1089 0.8008
3.750 0.3876 0.00811 0.00201 0.0053 0.0822 0.8189
4.000 0.4127 0.00830 0.00219 0.0058 0.0627 0.8377
4.250 0.4377 0.00846 0.00238 0.0064 0.0498 0.8582
4.500 0.4627 0.00862 0.00257 0.0070 0.0398 0.8815
4.750 0.4882 0.00877 0.00278 0.0075 0.0325 0.9061
5.000 0.5157 0.00897 0.00301 0.0075 0.0272 0.9293
5.250 0.5474 0.00918 0.00326 0.0066 0.0234 0.9476
5.500 0.5817 0.00947 0.00354 0.0050 0.0196 0.9610
5.750 0.6157 0.00974 0.00383 0.0035 0.0171 0.9710
6.000 0.6498 0.01003 0.00414 0.0019 0.0153 0.9777
6.250 0.6811 0.01038 0.00448 0.0009 0.0134 0.9837
6.500 0.7138 0.01069 0.00482 -0.0003 0.0124 0.9881
6.750 0.7441 0.01099 0.00514 -0.0011 0.0113 0.9931
7.000 0.7744 0.01134 0.00550 -0.0019 0.0103 0.9975
7.250 0.8047 0.01180 0.00598 -0.0027 0.0094 1.0000
7.500 0.8263 0.01216 0.00638 -0.0016 0.0090 1.0000
7.750 0.8483 0.01251 0.00677 -0.0006 0.0086 1.0000
8.000 0.8701 0.01288 0.00719 0.0004 0.0083 1.0000
8.250 0.8919 0.01328 0.00762 0.0015 0.0079 1.0000
8.500 0.9135 0.01369 0.00809 0.0025 0.0075 1.0000
8.750 0.9350 0.01412 0.00855 0.0035 0.0072 1.0000
9.000 0.9559 0.01462 0.00909 0.0046 0.0069 1.0000
9.250 0.9756 0.01527 0.00980 0.0059 0.0065 1.0000
9.500 0.9952 0.01593 0.01054 0.0071 0.0062 1.0000
9.750 1.0151 0.01656 0.01125 0.0083 0.0061 1.0000
10.000 1.0360 0.01706 0.01181 0.0092 0.0060 1.0000
10.250 1.0563 0.01761 0.01245 0.0103 0.0058 1.0000
10.500 1.0759 0.01823 0.01315 0.0114 0.0056 1.0000
10.750 1.0951 0.01888 0.01387 0.0125 0.0054 1.0000
11.000 1.1134 0.01959 0.01466 0.0137 0.0052 1.0000
11.250 1.1314 0.02029 0.01545 0.0149 0.0051 1.0000
11.500 1.1477 0.02113 0.01638 0.0164 0.0050 1.0000
11.750 1.1646 0.02185 0.01718 0.0177 0.0048 1.0000
12.000 1.1792 0.02273 0.01815 0.0192 0.0047 1.0000
12.250 1.1929 0.02362 0.01915 0.0209 0.0046 1.0000
12.500 1.2035 0.02464 0.02027 0.0229 0.0045 1.0000
12.750 1.2091 0.02569 0.02142 0.0257 0.0044 1.0000
13.000 1.2085 0.02714 0.02301 0.0289 0.0043 1.0000
13.250 1.2116 0.02847 0.02445 0.0312 0.0043 1.0000
13.500 1.2017 0.03093 0.02710 0.0338 0.0041 1.0000
13.750 1.1968 0.03326 0.02960 0.0352 0.0041 1.0000
14.000 1.1908 0.03600 0.03250 0.0359 0.0041 1.0000
14.250 1.1865 0.03886 0.03550 0.0358 0.0041 1.0000
14.500 1.1882 0.04132 0.03807 0.0354 0.0040 1.0000
14.750 1.1768 0.04563 0.04255 0.0338 0.0040 1.0000
15.000 1.1603 0.05109 0.04819 0.0312 0.0040 1.0000
15.250 1.1435 0.05711 0.05437 0.0278 0.0040 1.0000
15.500 1.1427 0.06096 0.05831 0.0255 0.0040 1.0000
15.750 1.0952 0.07366 0.07125 0.0174 0.0040 1.0000
16.000 1.0347 0.09114 0.08898 0.0068 0.0041 1.0000
16.250 1.0050 0.10209 0.10004 0.0012 0.0042 1.0000
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