RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 100 AIRFOIL (rae100-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.77 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae100-il-1000000-n5.txt Download as CSV file: xf-rae100-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1713 0.09934 0.09655 -0.0009 1.0000 0.0073
-17.500 -1.2201 0.08656 0.08359 -0.0081 1.0000 0.0072
-17.250 -1.2618 0.07556 0.07241 -0.0143 1.0000 0.0070
-17.000 -1.2925 0.06662 0.06332 -0.0195 1.0000 0.0071
-16.750 -1.3188 0.05860 0.05514 -0.0243 1.0000 0.0071
-16.500 -1.3360 0.05223 0.04862 -0.0281 1.0000 0.0071
-16.250 -1.3524 0.04628 0.04251 -0.0316 1.0000 0.0071
-16.000 -1.3603 0.04192 0.03803 -0.0340 1.0000 0.0072
-15.750 -1.3649 0.03832 0.03431 -0.0355 1.0000 0.0073
-15.500 -1.3690 0.03516 0.03103 -0.0365 1.0000 0.0074
-15.250 -1.3697 0.03271 0.02847 -0.0366 1.0000 0.0075
-15.000 -1.3694 0.03066 0.02631 -0.0360 1.0000 0.0076
-14.750 -1.3690 0.02887 0.02441 -0.0348 1.0000 0.0076
-14.500 -1.3666 0.02744 0.02288 -0.0331 1.0000 0.0077
-14.250 -1.3625 0.02626 0.02161 -0.0310 1.0000 0.0079
-14.000 -1.3576 0.02524 0.02050 -0.0285 1.0000 0.0080
-13.750 -1.3510 0.02436 0.01954 -0.0259 1.0000 0.0081
-13.500 -1.3393 0.02356 0.01865 -0.0240 1.0000 0.0082
-13.250 -1.3252 0.02278 0.01779 -0.0225 1.0000 0.0083
-13.000 -1.3125 0.02179 0.01672 -0.0208 1.0000 0.0086
-12.750 -1.2964 0.02101 0.01589 -0.0194 1.0000 0.0090
-12.500 -1.2790 0.02030 0.01512 -0.0182 1.0000 0.0093
-12.250 -1.2604 0.01965 0.01441 -0.0171 1.0000 0.0095
-12.000 -1.2410 0.01902 0.01372 -0.0160 1.0000 0.0098
-11.750 -1.2211 0.01843 0.01306 -0.0150 1.0000 0.0101
-11.500 -1.2005 0.01786 0.01244 -0.0141 1.0000 0.0104
-11.250 -1.1795 0.01732 0.01184 -0.0131 1.0000 0.0106
-11.000 -1.1577 0.01684 0.01130 -0.0123 1.0000 0.0109
-10.750 -1.1369 0.01622 0.01063 -0.0113 1.0000 0.0114
-10.500 -1.1151 0.01570 0.01006 -0.0105 1.0000 0.0119
-10.250 -1.0927 0.01523 0.00957 -0.0097 1.0000 0.0124
-10.000 -1.0699 0.01480 0.00910 -0.0089 1.0000 0.0129
-9.750 -1.0468 0.01440 0.00866 -0.0082 1.0000 0.0135
-9.500 -1.0233 0.01404 0.00825 -0.0075 1.0000 0.0139
-9.250 -1.0006 0.01357 0.00776 -0.0066 1.0000 0.0148
-9.000 -0.9773 0.01318 0.00736 -0.0059 1.0000 0.0157
-8.750 -0.9538 0.01282 0.00698 -0.0051 1.0000 0.0165
-8.500 -0.9300 0.01250 0.00662 -0.0044 1.0000 0.0173
-8.250 -0.9064 0.01216 0.00625 -0.0036 1.0000 0.0182
-8.000 -0.8830 0.01181 0.00591 -0.0028 1.0000 0.0197
-7.750 -0.8592 0.01151 0.00559 -0.0020 1.0000 0.0210
-7.500 -0.8352 0.01124 0.00530 -0.0012 1.0000 0.0222
-7.250 -0.8116 0.01092 0.00498 -0.0004 1.0000 0.0242
-7.000 -0.7878 0.01064 0.00471 0.0004 1.0000 0.0260
-6.750 -0.7638 0.01040 0.00445 0.0012 1.0000 0.0278
-6.500 -0.7403 0.01011 0.00418 0.0021 1.0000 0.0310
-6.250 -0.7165 0.00988 0.00395 0.0030 1.0000 0.0336
-6.000 -0.6839 0.00959 0.00370 0.0019 0.9975 0.0380
-5.750 -0.6514 0.00935 0.00346 0.0008 0.9934 0.0426
-5.500 -0.6202 0.00908 0.00323 0.0001 0.9882 0.0490
-5.250 -0.5865 0.00882 0.00302 -0.0012 0.9835 0.0562
-5.000 -0.5537 0.00857 0.00281 -0.0023 0.9767 0.0654
-4.750 -0.5183 0.00832 0.00260 -0.0039 0.9686 0.0763
-4.500 -0.4826 0.00805 0.00240 -0.0057 0.9557 0.0907
-4.250 -0.4490 0.00782 0.00221 -0.0069 0.9349 0.1062
-4.000 -0.4200 0.00764 0.00203 -0.0070 0.9063 0.1233
-3.750 -0.3942 0.00752 0.00188 -0.0064 0.8742 0.1400
-3.500 -0.3692 0.00740 0.00174 -0.0056 0.8415 0.1597
-3.250 -0.3440 0.00729 0.00160 -0.0050 0.8112 0.1818
-3.000 -0.3185 0.00719 0.00149 -0.0044 0.7828 0.2035
-2.750 -0.2926 0.00709 0.00138 -0.0039 0.7561 0.2267
-2.500 -0.2666 0.00698 0.00128 -0.0034 0.7310 0.2509
-2.250 -0.2404 0.00689 0.00119 -0.0030 0.7066 0.2757
-2.000 -0.2140 0.00680 0.00112 -0.0026 0.6823 0.3012
-1.750 -0.1876 0.00673 0.00105 -0.0022 0.6590 0.3257
-1.500 -0.1609 0.00666 0.00100 -0.0019 0.6361 0.3506
-1.250 -0.1343 0.00660 0.00095 -0.0015 0.6127 0.3768
-1.000 -0.1075 0.00655 0.00091 -0.0012 0.5898 0.4010
-0.500 -0.0538 0.00649 0.00086 -0.0006 0.5438 0.4495
-0.250 -0.0269 0.00649 0.00085 -0.0003 0.5207 0.4732
0.000 0.0000 0.00647 0.00084 0.0000 0.4968 0.4967
0.250 0.0269 0.00649 0.00085 0.0003 0.4725 0.5206
0.500 0.0538 0.00649 0.00086 0.0006 0.4495 0.5438
1.000 0.1074 0.00656 0.00091 0.0012 0.4006 0.5898
1.250 0.1343 0.00661 0.00095 0.0015 0.3764 0.6127
1.750 0.1876 0.00673 0.00105 0.0022 0.3259 0.6590
2.000 0.2140 0.00680 0.00112 0.0026 0.3018 0.6826
2.250 0.2404 0.00690 0.00119 0.0030 0.2755 0.7066
2.500 0.2666 0.00698 0.00128 0.0034 0.2509 0.7312
2.750 0.2926 0.00708 0.00138 0.0039 0.2269 0.7563
3.000 0.3184 0.00718 0.00148 0.0044 0.2037 0.7831
3.250 0.3439 0.00729 0.00160 0.0050 0.1817 0.8111
3.500 0.3692 0.00740 0.00174 0.0056 0.1601 0.8415
3.750 0.3942 0.00752 0.00188 0.0064 0.1401 0.8740
4.000 0.4200 0.00764 0.00203 0.0070 0.1233 0.9061
4.250 0.4489 0.00782 0.00221 0.0069 0.1065 0.9348
4.500 0.4826 0.00805 0.00240 0.0057 0.0907 0.9557
4.750 0.5184 0.00832 0.00260 0.0039 0.0761 0.9687
5.000 0.5536 0.00857 0.00281 0.0023 0.0651 0.9766
5.250 0.5863 0.00882 0.00302 0.0013 0.0562 0.9835
5.500 0.6200 0.00908 0.00323 0.0000 0.0491 0.9882
5.750 0.6512 0.00934 0.00346 -0.0008 0.0427 0.9933
6.000 0.6837 0.00959 0.00370 -0.0018 0.0380 0.9973
6.250 0.7166 0.00988 0.00395 -0.0030 0.0336 1.0000
6.500 0.7406 0.01011 0.00418 -0.0022 0.0312 1.0000
6.750 0.7640 0.01040 0.00445 -0.0013 0.0279 1.0000
7.000 0.7880 0.01064 0.00471 -0.0005 0.0260 1.0000
7.250 0.8118 0.01092 0.00498 0.0003 0.0242 1.0000
7.500 0.8353 0.01124 0.00531 0.0012 0.0221 1.0000
7.750 0.8593 0.01151 0.00560 0.0020 0.0210 1.0000
8.000 0.8830 0.01181 0.00591 0.0028 0.0196 1.0000
8.250 0.9064 0.01216 0.00626 0.0036 0.0182 1.0000
8.500 0.9300 0.01250 0.00662 0.0044 0.0173 1.0000
8.750 0.9538 0.01282 0.00698 0.0051 0.0165 1.0000
9.000 0.9773 0.01318 0.00736 0.0059 0.0157 1.0000
9.250 1.0005 0.01357 0.00776 0.0067 0.0149 1.0000
9.500 1.0232 0.01404 0.00825 0.0075 0.0140 1.0000
9.750 1.0466 0.01441 0.00867 0.0082 0.0135 1.0000
10.000 1.0697 0.01480 0.00910 0.0090 0.0130 1.0000
10.250 1.0925 0.01523 0.00956 0.0097 0.0124 1.0000
10.500 1.1149 0.01569 0.01007 0.0105 0.0120 1.0000
10.750 1.1366 0.01621 0.01062 0.0114 0.0114 1.0000
11.000 1.1575 0.01683 0.01128 0.0124 0.0109 1.0000
11.250 1.1792 0.01731 0.01183 0.0132 0.0107 1.0000
11.500 1.2001 0.01787 0.01244 0.0141 0.0104 1.0000
11.750 1.2207 0.01841 0.01305 0.0151 0.0101 1.0000
12.000 1.2409 0.01899 0.01369 0.0161 0.0098 1.0000
12.250 1.2603 0.01960 0.01436 0.0171 0.0095 1.0000
12.500 1.2787 0.02027 0.01509 0.0183 0.0093 1.0000
12.750 1.2962 0.02098 0.01585 0.0195 0.0090 1.0000
13.000 1.3121 0.02177 0.01671 0.0209 0.0087 1.0000
13.250 1.3249 0.02275 0.01776 0.0226 0.0083 1.0000
13.500 1.3388 0.02354 0.01863 0.0241 0.0082 1.0000
13.750 1.3504 0.02434 0.01952 0.0261 0.0081 1.0000
14.000 1.3574 0.02520 0.02046 0.0286 0.0080 1.0000
14.250 1.3618 0.02625 0.02160 0.0311 0.0079 1.0000
14.500 1.3660 0.02742 0.02287 0.0332 0.0078 1.0000
14.750 1.3684 0.02886 0.02441 0.0349 0.0076 1.0000
15.000 1.3691 0.03063 0.02628 0.0361 0.0075 1.0000
15.250 1.3700 0.03263 0.02838 0.0367 0.0074 1.0000
15.500 1.3694 0.03507 0.03093 0.0366 0.0073 1.0000
15.750 1.3664 0.03810 0.03407 0.0357 0.0072 1.0000
16.000 1.3606 0.04183 0.03793 0.0341 0.0072 1.0000
16.250 1.3520 0.04630 0.04253 0.0316 0.0071 1.0000
16.500 1.3402 0.05156 0.04793 0.0285 0.0071 1.0000
16.750 1.3178 0.05876 0.05530 0.0241 0.0071 1.0000
17.000 1.2937 0.06645 0.06314 0.0195 0.0071 1.0000
17.250 1.2627 0.07543 0.07228 0.0143 0.0071 1.0000
17.500 1.2209 0.08649 0.08352 0.0080 0.0072 1.0000
17.750 1.1744 0.09885 0.09605 0.0011 0.0072 1.0000
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Polar data table (+)
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