RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 100 AIRFOIL (rae100-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.08 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae100-il-1000000.txt Download as CSV file: xf-rae100-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9987 0.13801 0.13591 0.0213 1.0000 0.0103
-17.750 -1.0351 0.12523 0.12298 0.0140 1.0000 0.0102
-17.500 -1.0689 0.11379 0.11139 0.0075 1.0000 0.0101
-17.250 -1.0954 0.10428 0.10176 0.0022 1.0000 0.0100
-17.000 -1.1184 0.09570 0.09306 -0.0027 1.0000 0.0101
-16.750 -1.1472 0.08641 0.08365 -0.0079 1.0000 0.0100
-16.500 -1.1692 0.07866 0.07578 -0.0123 1.0000 0.0101
-16.250 -1.1972 0.07022 0.06719 -0.0171 1.0000 0.0100
-16.000 -1.2155 0.06336 0.06020 -0.0212 1.0000 0.0101
-15.750 -1.2304 0.05725 0.05396 -0.0248 1.0000 0.0101
-15.500 -1.2450 0.05134 0.04790 -0.0284 1.0000 0.0101
-15.250 -1.2542 0.04647 0.04290 -0.0312 1.0000 0.0102
-15.000 -1.2593 0.04243 0.03873 -0.0334 1.0000 0.0103
-14.750 -1.2672 0.03844 0.03460 -0.0351 1.0000 0.0103
-14.500 -1.2704 0.03538 0.03140 -0.0359 1.0000 0.0104
-14.250 -1.2698 0.03306 0.02897 -0.0360 1.0000 0.0106
-14.000 -1.2699 0.03098 0.02677 -0.0353 1.0000 0.0107
-13.750 -1.2672 0.02939 0.02507 -0.0341 1.0000 0.0108
-13.500 -1.2628 0.02808 0.02366 -0.0325 1.0000 0.0109
-13.250 -1.2691 0.02629 0.02173 -0.0292 1.0000 0.0111
-13.000 -1.2741 0.02471 0.02003 -0.0253 1.0000 0.0113
-12.750 -1.2657 0.02356 0.01882 -0.0232 1.0000 0.0117
-12.500 -1.2518 0.02270 0.01789 -0.0216 1.0000 0.0120
-12.250 -1.2350 0.02200 0.01714 -0.0204 1.0000 0.0123
-12.000 -1.2181 0.02125 0.01632 -0.0191 1.0000 0.0127
-11.750 -1.2001 0.02055 0.01555 -0.0179 1.0000 0.0131
-11.500 -1.1816 0.01984 0.01477 -0.0167 1.0000 0.0134
-11.250 -1.1618 0.01923 0.01407 -0.0157 1.0000 0.0137
-11.000 -1.1405 0.01875 0.01353 -0.0148 1.0000 0.0139
-10.750 -1.1267 0.01744 0.01210 -0.0130 1.0000 0.0146
-10.500 -1.1067 0.01674 0.01137 -0.0119 1.0000 0.0153
-10.250 -1.0848 0.01624 0.01083 -0.0111 1.0000 0.0159
-10.000 -1.0626 0.01575 0.01030 -0.0102 1.0000 0.0165
-9.750 -1.0400 0.01530 0.00980 -0.0094 1.0000 0.0171
-9.500 -1.0163 0.01497 0.00941 -0.0087 1.0000 0.0176
-9.250 -0.9969 0.01412 0.00851 -0.0075 1.0000 0.0189
-9.000 -0.9739 0.01369 0.00807 -0.0066 1.0000 0.0199
-8.750 -0.9506 0.01331 0.00766 -0.0059 1.0000 0.0209
-8.500 -0.9268 0.01298 0.00728 -0.0051 1.0000 0.0218
-8.250 -0.9050 0.01242 0.00668 -0.0040 1.0000 0.0233
-8.000 -0.8818 0.01202 0.00628 -0.0032 1.0000 0.0250
-7.750 -0.8580 0.01172 0.00596 -0.0024 1.0000 0.0266
-7.500 -0.8348 0.01135 0.00557 -0.0015 1.0000 0.0285
-7.250 -0.8117 0.01096 0.00519 -0.0006 1.0000 0.0312
-7.000 -0.7877 0.01070 0.00491 0.0002 1.0000 0.0333
-6.750 -0.7647 0.01033 0.00454 0.0012 1.0000 0.0370
-6.500 -0.7411 0.01005 0.00427 0.0021 1.0000 0.0406
-6.250 -0.7179 0.00973 0.00397 0.0030 1.0000 0.0458
-6.000 -0.6943 0.00949 0.00374 0.0040 1.0000 0.0504
-5.750 -0.6715 0.00917 0.00348 0.0050 1.0000 0.0585
-5.500 -0.6485 0.00890 0.00324 0.0060 1.0000 0.0675
-5.250 -0.6257 0.00864 0.00304 0.0070 1.0000 0.0781
-5.000 -0.6032 0.00839 0.00284 0.0081 1.0000 0.0907
-4.750 -0.5727 0.00810 0.00264 0.0074 0.9987 0.1088
-4.500 -0.5364 0.00781 0.00246 0.0055 0.9959 0.1311
-4.250 -0.5007 0.00752 0.00229 0.0038 0.9926 0.1570
-4.000 -0.4661 0.00722 0.00211 0.0023 0.9882 0.1852
-3.750 -0.4299 0.00693 0.00196 0.0004 0.9843 0.2161
-3.500 -0.3960 0.00666 0.00182 -0.0009 0.9781 0.2479
-3.250 -0.3598 0.00639 0.00168 -0.0027 0.9714 0.2822
-3.000 -0.3254 0.00615 0.00156 -0.0041 0.9603 0.3147
-2.750 -0.2911 0.00594 0.00145 -0.0054 0.9448 0.3470
-2.500 -0.2606 0.00577 0.00134 -0.0058 0.9218 0.3777
-2.250 -0.2336 0.00565 0.00125 -0.0053 0.8934 0.4068
-2.000 -0.2080 0.00558 0.00117 -0.0046 0.8626 0.4345
-1.750 -0.1826 0.00554 0.00111 -0.0039 0.8323 0.4614
-1.500 -0.1568 0.00550 0.00106 -0.0032 0.8031 0.4887
-1.250 -0.1311 0.00546 0.00101 -0.0026 0.7748 0.5162
-1.000 -0.1051 0.00543 0.00098 -0.0020 0.7483 0.5422
-0.750 -0.0790 0.00542 0.00095 -0.0015 0.7220 0.5681
-0.500 -0.0526 0.00540 0.00094 -0.0010 0.6962 0.5942
-0.250 -0.0264 0.00539 0.00092 -0.0005 0.6711 0.6196
0.000 0.0000 0.00540 0.00092 0.0000 0.6450 0.6450
0.250 0.0263 0.00539 0.00092 0.0005 0.6191 0.6710
0.500 0.0526 0.00540 0.00094 0.0010 0.5942 0.6962
0.750 0.0789 0.00542 0.00095 0.0015 0.5682 0.7220
1.000 0.1050 0.00544 0.00098 0.0020 0.5419 0.7483
1.250 0.1310 0.00546 0.00101 0.0026 0.5159 0.7749
1.500 0.1568 0.00550 0.00106 0.0032 0.4886 0.8031
2.000 0.2080 0.00558 0.00117 0.0046 0.4351 0.8627
2.250 0.2336 0.00565 0.00125 0.0053 0.4067 0.8934
2.500 0.2605 0.00577 0.00134 0.0058 0.3776 0.9219
2.750 0.2911 0.00593 0.00145 0.0054 0.3472 0.9448
3.000 0.3254 0.00615 0.00156 0.0041 0.3148 0.9603
3.250 0.3597 0.00639 0.00168 0.0027 0.2820 0.9714
3.500 0.3959 0.00665 0.00182 0.0009 0.2486 0.9780
3.750 0.4297 0.00693 0.00196 -0.0004 0.2163 0.9842
4.000 0.4660 0.00722 0.00211 -0.0022 0.1853 0.9881
4.250 0.5006 0.00752 0.00229 -0.0038 0.1568 0.9926
4.500 0.5363 0.00781 0.00246 -0.0055 0.1313 0.9958
4.750 0.5726 0.00810 0.00264 -0.0074 0.1087 0.9987
5.000 0.6035 0.00839 0.00284 -0.0082 0.0904 1.0000
5.250 0.6260 0.00865 0.00304 -0.0071 0.0779 1.0000
5.500 0.6489 0.00890 0.00325 -0.0061 0.0676 1.0000
5.750 0.6718 0.00918 0.00348 -0.0050 0.0585 1.0000
6.000 0.6946 0.00949 0.00374 -0.0040 0.0504 1.0000
6.250 0.7182 0.00973 0.00398 -0.0031 0.0458 1.0000
6.500 0.7413 0.01006 0.00428 -0.0021 0.0407 1.0000
6.750 0.7649 0.01033 0.00454 -0.0013 0.0369 1.0000
7.000 0.7879 0.01070 0.00491 -0.0003 0.0333 1.0000
7.250 0.8119 0.01096 0.00519 0.0005 0.0311 1.0000
7.500 0.8349 0.01136 0.00557 0.0015 0.0284 1.0000
7.750 0.8581 0.01173 0.00597 0.0024 0.0266 1.0000
8.000 0.8820 0.01202 0.00628 0.0032 0.0250 1.0000
8.250 0.9050 0.01242 0.00668 0.0040 0.0233 1.0000
8.500 0.9268 0.01299 0.00729 0.0051 0.0218 1.0000
8.750 0.9505 0.01332 0.00766 0.0059 0.0210 1.0000
9.000 0.9738 0.01369 0.00807 0.0067 0.0199 1.0000
9.250 0.9968 0.01411 0.00851 0.0075 0.0189 1.0000
9.500 1.0161 0.01496 0.00940 0.0088 0.0176 1.0000
9.750 1.0395 0.01532 0.00982 0.0095 0.0171 1.0000
10.000 1.0622 0.01576 0.01031 0.0103 0.0165 1.0000
10.250 1.0846 0.01622 0.01082 0.0111 0.0158 1.0000
10.500 1.1062 0.01676 0.01139 0.0120 0.0153 1.0000
10.750 1.1265 0.01741 0.01208 0.0130 0.0147 1.0000
11.000 1.1405 0.01869 0.01347 0.0148 0.0139 1.0000
11.250 1.1616 0.01921 0.01405 0.0157 0.0137 1.0000
11.500 1.1805 0.01990 0.01483 0.0169 0.0135 1.0000
11.750 1.1997 0.02053 0.01553 0.0180 0.0131 1.0000
12.000 1.2180 0.02121 0.01628 0.0191 0.0126 1.0000
12.250 1.2358 0.02187 0.01701 0.0203 0.0123 1.0000
12.500 1.2520 0.02263 0.01782 0.0217 0.0119 1.0000
12.750 1.2658 0.02350 0.01875 0.0232 0.0117 1.0000
13.000 1.2733 0.02471 0.02004 0.0255 0.0113 1.0000
13.250 1.2679 0.02632 0.02176 0.0294 0.0110 1.0000
13.500 1.2612 0.02816 0.02375 0.0326 0.0109 1.0000
13.750 1.2665 0.02940 0.02509 0.0342 0.0108 1.0000
14.000 1.2706 0.03089 0.02667 0.0354 0.0107 1.0000
14.250 1.2692 0.03308 0.02899 0.0360 0.0106 1.0000
14.500 1.2686 0.03553 0.03155 0.0359 0.0105 1.0000
14.750 1.2639 0.03879 0.03495 0.0350 0.0104 1.0000
15.000 1.2586 0.04252 0.03883 0.0333 0.0103 1.0000
15.250 1.2543 0.04646 0.04289 0.0312 0.0102 1.0000
15.500 1.2456 0.05128 0.04784 0.0283 0.0101 1.0000
15.750 1.2335 0.05682 0.05352 0.0250 0.0100 1.0000
16.000 1.2156 0.06341 0.06025 0.0211 0.0100 1.0000
16.250 1.1954 0.07057 0.06755 0.0168 0.0099 1.0000
16.500 1.1749 0.07782 0.07492 0.0127 0.0100 1.0000
16.750 1.1429 0.08713 0.08439 0.0074 0.0102 1.0000
17.000 1.1205 0.09534 0.09271 0.0028 0.0101 1.0000
17.250 1.0965 0.10409 0.10158 -0.0022 0.0101 1.0000
17.500 1.0664 0.11442 0.11204 -0.0080 0.0101 1.0000
17.750 1.0362 0.12520 0.12294 -0.0141 0.0101 1.0000
18.000 0.9974 0.13855 0.13645 -0.0217 0.0103 1.0000
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