RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 101 AIRFOIL (rae101-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.18 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae101-il-1000000-n5.txt Download as CSV file: xf-rae101-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 101 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
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0787 0.09699 0.09471 -0.0019 1.0000 0.0046
-16.500 -1.1235 0.08363 0.08117 -0.0095 1.0000 0.0046
-16.250 -1.1756 0.07008 0.06738 -0.0176 1.0000 0.0044
-16.000 -1.1969 0.06265 0.05980 -0.0220 1.0000 0.0044
-15.750 -1.2151 0.05605 0.05305 -0.0259 1.0000 0.0044
-15.500 -1.2289 0.05046 0.04731 -0.0291 1.0000 0.0044
-15.250 -1.2406 0.04551 0.04221 -0.0317 1.0000 0.0045
-15.000 -1.2463 0.04171 0.03829 -0.0334 1.0000 0.0045
-14.750 -1.2517 0.03826 0.03470 -0.0345 1.0000 0.0045
-14.500 -1.2554 0.03533 0.03164 -0.0349 1.0000 0.0046
-14.250 -1.2551 0.03309 0.02929 -0.0346 1.0000 0.0047
-14.000 -1.2540 0.03116 0.02725 -0.0338 1.0000 0.0048
-13.750 -1.2533 0.02941 0.02538 -0.0325 1.0000 0.0048
-13.500 -1.2510 0.02796 0.02382 -0.0306 1.0000 0.0049
-13.250 -1.2479 0.02669 0.02244 -0.0283 1.0000 0.0050
-13.000 -1.2433 0.02562 0.02126 -0.0257 1.0000 0.0050
-12.750 -1.2371 0.02463 0.02017 -0.0230 1.0000 0.0051
-12.500 -1.2263 0.02364 0.01907 -0.0211 1.0000 0.0052
-12.250 -1.2125 0.02276 0.01809 -0.0195 1.0000 0.0053
-12.000 -1.1970 0.02196 0.01720 -0.0180 1.0000 0.0055
-11.750 -1.1801 0.02122 0.01637 -0.0168 1.0000 0.0056
-11.500 -1.1625 0.02050 0.01557 -0.0155 1.0000 0.0057
-11.250 -1.1457 0.01966 0.01462 -0.0142 1.0000 0.0058
-11.000 -1.1298 0.01866 0.01353 -0.0127 1.0000 0.0061
-10.750 -1.1110 0.01793 0.01272 -0.0116 1.0000 0.0063
-10.500 -1.0909 0.01731 0.01204 -0.0105 1.0000 0.0065
-10.250 -1.0703 0.01674 0.01141 -0.0096 1.0000 0.0067
-10.000 -1.0492 0.01620 0.01082 -0.0086 1.0000 0.0070
-9.750 -1.0279 0.01567 0.01023 -0.0077 1.0000 0.0072
-9.500 -1.0062 0.01518 0.00968 -0.0068 1.0000 0.0075
-9.250 -0.9844 0.01470 0.00914 -0.0059 1.0000 0.0078
-9.000 -0.9622 0.01426 0.00864 -0.0050 1.0000 0.0081
-8.750 -0.9398 0.01385 0.00818 -0.0042 1.0000 0.0082
-8.500 -0.9186 0.01329 0.00758 -0.0031 1.0000 0.0088
-8.250 -0.8964 0.01287 0.00712 -0.0021 1.0000 0.0093
-8.000 -0.8739 0.01249 0.00673 -0.0013 1.0000 0.0098
-7.750 -0.8510 0.01216 0.00636 -0.0004 1.0000 0.0105
-7.500 -0.8280 0.01184 0.00600 0.0005 1.0000 0.0111
-7.250 -0.8049 0.01153 0.00567 0.0013 1.0000 0.0116
-7.000 -0.7826 0.01115 0.00528 0.0023 1.0000 0.0128
-6.750 -0.7599 0.01084 0.00497 0.0033 1.0000 0.0138
-6.500 -0.7310 0.01055 0.00465 0.0029 0.9985 0.0149
-6.250 -0.6987 0.01026 0.00434 0.0018 0.9948 0.0161
-6.000 -0.6682 0.00994 0.00403 0.0010 0.9898 0.0186
-5.750 -0.6356 0.00968 0.00376 -0.0002 0.9847 0.0206
-5.500 -0.6027 0.00939 0.00348 -0.0014 0.9784 0.0240
-5.250 -0.5676 0.00913 0.00323 -0.0031 0.9708 0.0275
-5.000 -0.5329 0.00886 0.00298 -0.0047 0.9593 0.0339
-4.750 -0.4978 0.00861 0.00274 -0.0064 0.9426 0.0412
-4.500 -0.4675 0.00841 0.00252 -0.0069 0.9177 0.0506
-4.250 -0.4413 0.00823 0.00231 -0.0065 0.8884 0.0641
-4.000 -0.4163 0.00807 0.00213 -0.0059 0.8601 0.0801
-3.750 -0.3916 0.00789 0.00194 -0.0052 0.8338 0.1032
-3.500 -0.3669 0.00767 0.00176 -0.0046 0.8099 0.1344
-3.250 -0.3422 0.00741 0.00158 -0.0040 0.7873 0.1758
-3.000 -0.3175 0.00714 0.00141 -0.0035 0.7664 0.2219
-2.750 -0.2931 0.00680 0.00124 -0.0029 0.7479 0.2844
-2.500 -0.2679 0.00654 0.00113 -0.0025 0.7295 0.3405
-2.250 -0.2419 0.00641 0.00104 -0.0021 0.7113 0.3737
-2.000 -0.2154 0.00630 0.00097 -0.0018 0.6947 0.4022
-1.500 -0.1620 0.00615 0.00087 -0.0013 0.6642 0.4513
-1.250 -0.1352 0.00609 0.00083 -0.0011 0.6486 0.4741
-1.000 -0.1083 0.00604 0.00080 -0.0008 0.6331 0.4966
-0.750 -0.0813 0.00599 0.00078 -0.0006 0.6190 0.5179
-0.500 -0.0542 0.00594 0.00076 -0.0004 0.6057 0.5394
-0.250 -0.0271 0.00592 0.00075 -0.0002 0.5920 0.5590
0.000 0.0000 0.00590 0.00075 0.0000 0.5764 0.5764
0.250 0.0270 0.00592 0.00075 0.0002 0.5589 0.5920
0.500 0.0542 0.00594 0.00076 0.0004 0.5394 0.6057
0.750 0.0813 0.00599 0.00078 0.0006 0.5181 0.6190
1.000 0.1083 0.00604 0.00080 0.0008 0.4965 0.6331
1.250 0.1351 0.00609 0.00083 0.0011 0.4741 0.6487
1.500 0.1620 0.00615 0.00087 0.0013 0.4515 0.6642
2.000 0.2154 0.00631 0.00097 0.0018 0.4016 0.6947
2.250 0.2418 0.00641 0.00104 0.0021 0.3734 0.7113
2.500 0.2679 0.00654 0.00113 0.0025 0.3410 0.7298
2.750 0.2931 0.00679 0.00124 0.0029 0.2855 0.7480
3.000 0.3175 0.00714 0.00141 0.0035 0.2232 0.7665
3.250 0.3422 0.00741 0.00158 0.0040 0.1764 0.7871
3.500 0.3669 0.00767 0.00176 0.0046 0.1342 0.8094
3.750 0.3917 0.00788 0.00194 0.0052 0.1046 0.8335
4.000 0.4163 0.00807 0.00213 0.0059 0.0802 0.8600
4.250 0.4413 0.00823 0.00231 0.0065 0.0643 0.8886
4.500 0.4674 0.00841 0.00252 0.0069 0.0502 0.9175
4.750 0.4977 0.00861 0.00274 0.0064 0.0413 0.9424
5.000 0.5328 0.00886 0.00298 0.0047 0.0336 0.9592
5.250 0.5678 0.00913 0.00323 0.0030 0.0275 0.9710
5.500 0.6029 0.00940 0.00348 0.0013 0.0238 0.9787
5.750 0.6357 0.00968 0.00376 0.0001 0.0206 0.9848
6.000 0.6684 0.00994 0.00403 -0.0011 0.0186 0.9899
6.250 0.6989 0.01027 0.00434 -0.0018 0.0161 0.9949
6.500 0.7312 0.01055 0.00465 -0.0029 0.0149 0.9987
6.750 0.7597 0.01084 0.00496 -0.0032 0.0138 1.0000
7.000 0.7825 0.01115 0.00528 -0.0023 0.0128 1.0000
7.250 0.8049 0.01152 0.00566 -0.0013 0.0117 1.0000
7.500 0.8278 0.01185 0.00602 -0.0004 0.0111 1.0000
7.750 0.8510 0.01215 0.00635 0.0004 0.0105 1.0000
8.000 0.8738 0.01249 0.00673 0.0013 0.0099 1.0000
8.250 0.8964 0.01287 0.00713 0.0022 0.0094 1.0000
8.500 0.9186 0.01329 0.00757 0.0031 0.0088 1.0000
8.750 0.9397 0.01386 0.00819 0.0042 0.0082 1.0000
9.000 0.9622 0.01426 0.00865 0.0050 0.0081 1.0000
9.250 0.9844 0.01471 0.00916 0.0059 0.0078 1.0000
9.500 1.0063 0.01519 0.00970 0.0068 0.0076 1.0000
9.750 1.0280 0.01568 0.01024 0.0077 0.0073 1.0000
10.000 1.0494 0.01620 0.01082 0.0086 0.0070 1.0000
10.250 1.0705 0.01675 0.01142 0.0095 0.0068 1.0000
10.500 1.0912 0.01732 0.01204 0.0105 0.0065 1.0000
10.750 1.1112 0.01795 0.01274 0.0115 0.0063 1.0000
11.000 1.1305 0.01862 0.01349 0.0126 0.0061 1.0000
11.250 1.1470 0.01956 0.01452 0.0140 0.0058 1.0000
11.500 1.1625 0.02054 0.01560 0.0155 0.0057 1.0000
11.750 1.1807 0.02120 0.01635 0.0167 0.0056 1.0000
12.000 1.1981 0.02190 0.01713 0.0179 0.0055 1.0000
12.250 1.2134 0.02272 0.01804 0.0193 0.0054 1.0000
12.500 1.2273 0.02360 0.01902 0.0209 0.0052 1.0000
12.750 1.2386 0.02458 0.02011 0.0228 0.0051 1.0000
13.000 1.2451 0.02555 0.02119 0.0254 0.0051 1.0000
13.250 1.2500 0.02661 0.02235 0.0280 0.0049 1.0000
13.500 1.2530 0.02789 0.02374 0.0304 0.0049 1.0000
13.750 1.2539 0.02943 0.02541 0.0323 0.0049 1.0000
14.000 1.2548 0.03118 0.02727 0.0337 0.0048 1.0000
14.250 1.2564 0.03308 0.02927 0.0345 0.0047 1.0000
14.500 1.2569 0.03530 0.03161 0.0347 0.0046 1.0000
14.750 1.2563 0.03789 0.03431 0.0344 0.0046 1.0000
15.000 1.2495 0.04149 0.03806 0.0332 0.0045 1.0000
15.250 1.2472 0.04484 0.04152 0.0318 0.0044 1.0000
15.500 1.2333 0.05007 0.04692 0.0291 0.0045 1.0000
15.750 1.2111 0.05697 0.05401 0.0251 0.0045 1.0000
16.000 1.1957 0.06318 0.06034 0.0214 0.0045 1.0000
16.250 1.1709 0.07127 0.06860 0.0165 0.0044 1.0000
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