RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 100 AIRFOIL (rae100-il) Reynolds number: 500,000 Max Cl/Cd: 60.92 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae100-il-500000-n5.txt Download as CSV file: xf-rae100-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9588 0.13975 0.13697 0.0234 1.0000 0.0105
-17.250 -0.9892 0.12798 0.12507 0.0168 1.0000 0.0105
-17.000 -1.0176 0.11714 0.11410 0.0106 1.0000 0.0105
-16.750 -1.0441 0.10720 0.10402 0.0050 1.0000 0.0105
-16.500 -1.0680 0.09817 0.09486 -0.0002 1.0000 0.0104
-16.250 -1.0940 0.08910 0.08566 -0.0054 1.0000 0.0104
-16.000 -1.1186 0.08068 0.07710 -0.0102 1.0000 0.0104
-15.750 -1.1384 0.07327 0.06956 -0.0145 1.0000 0.0104
-15.500 -1.1593 0.06587 0.06200 -0.0189 1.0000 0.0104
-15.250 -1.1751 0.05946 0.05544 -0.0228 1.0000 0.0105
-15.000 -1.1875 0.05382 0.04964 -0.0262 1.0000 0.0105
-14.750 -1.1990 0.04861 0.04429 -0.0292 1.0000 0.0105
-14.500 -1.2071 0.04418 0.03970 -0.0315 1.0000 0.0106
-14.250 -1.2122 0.04053 0.03589 -0.0331 1.0000 0.0107
-14.000 -1.2162 0.03737 0.03258 -0.0339 1.0000 0.0108
-13.750 -1.2176 0.03485 0.02993 -0.0340 1.0000 0.0109
-13.500 -1.2240 0.03226 0.02723 -0.0332 1.0000 0.0112
-13.250 -1.2246 0.03045 0.02531 -0.0317 1.0000 0.0113
-13.000 -1.2237 0.02895 0.02371 -0.0296 1.0000 0.0114
-12.750 -1.2196 0.02778 0.02245 -0.0272 1.0000 0.0117
-12.500 -1.2132 0.02674 0.02132 -0.0248 1.0000 0.0119
-12.250 -1.2019 0.02575 0.02023 -0.0231 1.0000 0.0122
-12.000 -1.1888 0.02478 0.01916 -0.0215 1.0000 0.0125
-11.750 -1.1743 0.02386 0.01814 -0.0201 1.0000 0.0129
-11.500 -1.1584 0.02297 0.01715 -0.0187 1.0000 0.0133
-11.250 -1.1410 0.02218 0.01625 -0.0175 1.0000 0.0137
-11.000 -1.1234 0.02136 0.01534 -0.0163 1.0000 0.0142
-10.750 -1.1057 0.02051 0.01442 -0.0151 1.0000 0.0147
-10.500 -1.0860 0.01982 0.01368 -0.0141 1.0000 0.0153
-10.250 -1.0656 0.01919 0.01299 -0.0131 1.0000 0.0160
-10.000 -1.0449 0.01856 0.01228 -0.0122 1.0000 0.0166
-9.750 -1.0237 0.01797 0.01160 -0.0113 1.0000 0.0172
-9.500 -1.0026 0.01733 0.01089 -0.0103 1.0000 0.0179
-9.250 -0.9813 0.01672 0.01025 -0.0094 1.0000 0.0189
-9.000 -0.9589 0.01622 0.00971 -0.0086 1.0000 0.0200
-8.750 -0.9362 0.01575 0.00918 -0.0078 1.0000 0.0211
-8.500 -0.9133 0.01529 0.00866 -0.0070 1.0000 0.0222
-8.250 -0.8911 0.01475 0.00810 -0.0061 1.0000 0.0237
-8.000 -0.8681 0.01431 0.00764 -0.0053 1.0000 0.0252
-7.750 -0.8447 0.01394 0.00721 -0.0045 1.0000 0.0269
-7.500 -0.8217 0.01349 0.00675 -0.0036 1.0000 0.0290
-7.250 -0.7985 0.01311 0.00636 -0.0028 1.0000 0.0315
-7.000 -0.7749 0.01279 0.00600 -0.0020 1.0000 0.0337
-6.750 -0.7519 0.01239 0.00561 -0.0011 1.0000 0.0371
-6.500 -0.7284 0.01207 0.00528 -0.0002 1.0000 0.0407
-6.250 -0.7051 0.01172 0.00495 0.0007 1.0000 0.0453
-6.000 -0.6816 0.01143 0.00466 0.0015 1.0000 0.0501
-5.750 -0.6584 0.01110 0.00436 0.0025 1.0000 0.0567
-5.500 -0.6351 0.01081 0.00409 0.0034 1.0000 0.0641
-5.250 -0.6118 0.01054 0.00384 0.0043 1.0000 0.0728
-5.000 -0.5889 0.01024 0.00360 0.0052 1.0000 0.0840
-4.500 -0.5220 0.00961 0.00312 0.0026 0.9898 0.1172
-4.250 -0.4878 0.00931 0.00291 0.0012 0.9838 0.1386
-4.000 -0.4550 0.00899 0.00270 0.0000 0.9758 0.1628
-3.750 -0.4201 0.00869 0.00251 -0.0015 0.9674 0.1902
-3.500 -0.3849 0.00840 0.00234 -0.0032 0.9561 0.2197
-3.250 -0.3497 0.00813 0.00217 -0.0047 0.9412 0.2505
-3.000 -0.3162 0.00788 0.00202 -0.0059 0.9206 0.2812
-2.500 -0.2584 0.00754 0.00175 -0.0060 0.8649 0.3403
-2.250 -0.2325 0.00745 0.00165 -0.0053 0.8349 0.3672
-2.000 -0.2070 0.00737 0.00156 -0.0046 0.8058 0.3951
-1.750 -0.1815 0.00730 0.00148 -0.0039 0.7782 0.4222
-1.500 -0.1559 0.00724 0.00142 -0.0033 0.7515 0.4482
-1.250 -0.1301 0.00720 0.00137 -0.0027 0.7255 0.4750
-1.000 -0.1042 0.00716 0.00132 -0.0021 0.7003 0.5009
-0.750 -0.0783 0.00713 0.00129 -0.0016 0.6754 0.5263
-0.500 -0.0522 0.00711 0.00127 -0.0011 0.6504 0.5516
-0.250 -0.0262 0.00710 0.00125 -0.0005 0.6261 0.5766
0.000 0.0000 0.00709 0.00125 0.0000 0.6012 0.6011
0.250 0.0261 0.00710 0.00125 0.0005 0.5766 0.6262
0.500 0.0521 0.00711 0.00127 0.0011 0.5516 0.6505
1.000 0.1042 0.00716 0.00132 0.0021 0.5010 0.7002
1.250 0.1301 0.00720 0.00137 0.0027 0.4749 0.7253
1.500 0.1559 0.00724 0.00142 0.0033 0.4483 0.7516
1.750 0.1815 0.00729 0.00148 0.0040 0.4223 0.7784
2.000 0.2070 0.00737 0.00156 0.0046 0.3951 0.8058
2.250 0.2325 0.00745 0.00165 0.0053 0.3675 0.8347
2.500 0.2583 0.00754 0.00175 0.0060 0.3399 0.8649
2.750 0.2855 0.00769 0.00188 0.0063 0.3109 0.8946
3.000 0.3161 0.00788 0.00202 0.0059 0.2808 0.9206
3.250 0.3497 0.00813 0.00217 0.0047 0.2502 0.9412
3.500 0.3849 0.00840 0.00234 0.0031 0.2193 0.9561
3.750 0.4201 0.00869 0.00252 0.0015 0.1900 0.9673
4.000 0.4550 0.00899 0.00270 0.0000 0.1627 0.9757
4.250 0.4877 0.00930 0.00291 -0.0011 0.1388 0.9837
4.500 0.5219 0.00960 0.00312 -0.0026 0.1176 0.9898
5.000 0.5891 0.01024 0.00360 -0.0053 0.0839 1.0000
5.250 0.6121 0.01054 0.00384 -0.0043 0.0726 1.0000
5.500 0.6353 0.01081 0.00409 -0.0034 0.0641 1.0000
5.750 0.6586 0.01110 0.00436 -0.0025 0.0567 1.0000
6.000 0.6818 0.01143 0.00466 -0.0016 0.0501 1.0000
6.250 0.7053 0.01172 0.00495 -0.0007 0.0454 1.0000
6.500 0.7285 0.01207 0.00528 0.0002 0.0408 1.0000
6.750 0.7520 0.01239 0.00562 0.0010 0.0371 1.0000
7.000 0.7750 0.01279 0.00600 0.0019 0.0337 1.0000
7.250 0.7986 0.01311 0.00637 0.0028 0.0315 1.0000
7.500 0.8218 0.01349 0.00675 0.0036 0.0290 1.0000
7.750 0.8447 0.01394 0.00721 0.0045 0.0269 1.0000
8.000 0.8680 0.01432 0.00764 0.0053 0.0252 1.0000
8.250 0.8911 0.01475 0.00810 0.0061 0.0237 1.0000
8.500 0.9133 0.01528 0.00865 0.0070 0.0222 1.0000
8.750 0.9360 0.01575 0.00918 0.0078 0.0212 1.0000
9.000 0.9587 0.01621 0.00970 0.0086 0.0200 1.0000
9.250 0.9811 0.01671 0.01024 0.0094 0.0189 1.0000
9.500 1.0024 0.01732 0.01088 0.0104 0.0180 1.0000
9.750 1.0232 0.01798 0.01161 0.0113 0.0173 1.0000
10.000 1.0444 0.01857 0.01229 0.0123 0.0167 1.0000
10.250 1.0652 0.01918 0.01298 0.0132 0.0160 1.0000
10.500 1.0855 0.01984 0.01370 0.0142 0.0154 1.0000
10.750 1.1053 0.02050 0.01442 0.0152 0.0147 1.0000
11.000 1.1230 0.02135 0.01533 0.0164 0.0141 1.0000
11.250 1.1407 0.02216 0.01622 0.0176 0.0137 1.0000
11.500 1.1576 0.02300 0.01717 0.0188 0.0134 1.0000
11.750 1.1738 0.02384 0.01812 0.0202 0.0129 1.0000
12.000 1.1888 0.02473 0.01911 0.0216 0.0125 1.0000
12.250 1.2022 0.02567 0.02014 0.0231 0.0122 1.0000
12.500 1.2130 0.02671 0.02129 0.0249 0.0119 1.0000
12.750 1.2196 0.02773 0.02240 0.0273 0.0117 1.0000
13.000 1.2236 0.02892 0.02367 0.0297 0.0114 1.0000
13.250 1.2251 0.03038 0.02523 0.0317 0.0113 1.0000
13.500 1.2232 0.03228 0.02724 0.0333 0.0111 1.0000
13.750 1.2176 0.03481 0.02989 0.0340 0.0109 1.0000
14.000 1.2159 0.03737 0.03257 0.0340 0.0108 1.0000
14.250 1.2123 0.04048 0.03584 0.0331 0.0107 1.0000
14.500 1.2070 0.04418 0.03969 0.0315 0.0106 1.0000
14.750 1.1980 0.04873 0.04441 0.0291 0.0105 1.0000
15.000 1.1876 0.05381 0.04964 0.0262 0.0105 1.0000
15.250 1.1759 0.05937 0.05536 0.0228 0.0104 1.0000
15.500 1.1595 0.06586 0.06200 0.0189 0.0104 1.0000
15.750 1.1401 0.07304 0.06932 0.0146 0.0104 1.0000
16.000 1.1181 0.08082 0.07725 0.0101 0.0104 1.0000
16.250 1.0940 0.08922 0.08579 0.0052 0.0103 1.0000
16.500 1.0706 0.09777 0.09447 0.0003 0.0104 1.0000
16.750 1.0443 0.10720 0.10402 -0.0051 0.0105 1.0000
17.000 1.0189 0.11696 0.11391 -0.0106 0.0105 1.0000
17.250 0.9934 0.12707 0.12415 -0.0163 0.0105 1.0000
17.500 0.9573 0.14030 0.13753 -0.0238 0.0105 1.0000
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Polar data table (+)
Polar graphs
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