Falcon (falcon-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Falcon (falcon-il) Reynolds number: 500,000 Max Cl/Cd: 78.59 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-falcon-il-500000-n5.txt Download as CSV file: xf-falcon-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Falcon
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8867 0.11589 0.11301 -0.0108 1.0000 0.0122
-16.500 -0.9969 0.08893 0.08565 -0.0256 1.0000 0.0118
-16.250 -1.0444 0.07557 0.07204 -0.0337 1.0000 0.0117
-16.000 -1.0739 0.06644 0.06271 -0.0393 1.0000 0.0117
-15.750 -1.0935 0.05953 0.05562 -0.0434 1.0000 0.0117
-15.500 -1.1074 0.05400 0.04992 -0.0463 1.0000 0.0118
-15.250 -1.1173 0.04945 0.04522 -0.0484 1.0000 0.0119
-15.000 -1.1235 0.04575 0.04138 -0.0495 1.0000 0.0120
-14.750 -1.1285 0.04250 0.03800 -0.0500 1.0000 0.0121
-14.500 -1.1311 0.03978 0.03513 -0.0499 1.0000 0.0122
-14.250 -1.1314 0.03748 0.03271 -0.0492 1.0000 0.0124
-14.000 -1.1312 0.03541 0.03050 -0.0481 1.0000 0.0126
-13.750 -1.1290 0.03364 0.02861 -0.0467 1.0000 0.0128
-13.500 -1.1256 0.03208 0.02693 -0.0450 1.0000 0.0130
-13.250 -1.1207 0.03073 0.02545 -0.0430 1.0000 0.0132
-13.000 -1.1149 0.02952 0.02412 -0.0408 1.0000 0.0134
-12.750 -1.1084 0.02844 0.02291 -0.0383 1.0000 0.0136
-12.500 -1.1042 0.02731 0.02169 -0.0352 1.0000 0.0138
-12.250 -1.1004 0.02629 0.02060 -0.0318 1.0000 0.0141
-12.000 -1.0924 0.02542 0.01966 -0.0289 1.0000 0.0144
-11.750 -1.0797 0.02461 0.01879 -0.0268 1.0000 0.0146
-11.500 -1.0660 0.02385 0.01796 -0.0247 1.0000 0.0149
-11.250 -1.0511 0.02315 0.01719 -0.0228 1.0000 0.0153
-11.000 -1.0357 0.02244 0.01641 -0.0209 1.0000 0.0156
-10.750 -1.0196 0.02176 0.01565 -0.0191 1.0000 0.0160
-10.500 -1.0029 0.02110 0.01491 -0.0173 1.0000 0.0164
-10.250 -0.9855 0.02048 0.01421 -0.0156 1.0000 0.0168
-10.000 -0.9674 0.01992 0.01357 -0.0140 1.0000 0.0171
-9.750 -0.9513 0.01918 0.01281 -0.0121 1.0000 0.0177
-9.500 -0.9330 0.01865 0.01225 -0.0105 1.0000 0.0183
-9.250 -0.9141 0.01817 0.01174 -0.0089 1.0000 0.0189
-9.000 -0.8953 0.01771 0.01123 -0.0073 1.0000 0.0195
-8.750 -0.8751 0.01724 0.01071 -0.0060 0.9997 0.0202
-8.250 -0.8201 0.01607 0.00945 -0.0065 0.9769 0.0216
-8.000 -0.7878 0.01550 0.00885 -0.0077 0.9707 0.0226
-7.750 -0.7529 0.01502 0.00834 -0.0095 0.9660 0.0239
-7.500 -0.7164 0.01456 0.00783 -0.0116 0.9614 0.0252
-7.250 -0.6778 0.01403 0.00727 -0.0142 0.9573 0.0267
-7.000 -0.6369 0.01353 0.00676 -0.0173 0.9531 0.0287
-6.750 -0.5963 0.01313 0.00631 -0.0203 0.9464 0.0309
-6.500 -0.5569 0.01268 0.00585 -0.0231 0.9384 0.0338
-6.250 -0.5216 0.01235 0.00548 -0.0249 0.9277 0.0369
-6.000 -0.4919 0.01205 0.00516 -0.0254 0.9148 0.0403
-5.750 -0.4641 0.01180 0.00488 -0.0254 0.9010 0.0447
-5.500 -0.4377 0.01154 0.00461 -0.0251 0.8856 0.0503
-5.250 -0.4119 0.01133 0.00437 -0.0246 0.8685 0.0566
-5.000 -0.3865 0.01113 0.00414 -0.0241 0.8497 0.0640
-4.750 -0.3617 0.01094 0.00391 -0.0234 0.8285 0.0721
-4.500 -0.3371 0.01080 0.00371 -0.0226 0.8051 0.0804
-4.250 -0.3128 0.01069 0.00352 -0.0217 0.7804 0.0893
-4.000 -0.2888 0.01057 0.00334 -0.0208 0.7555 0.0988
-3.750 -0.2647 0.01049 0.00318 -0.0199 0.7311 0.1076
-3.500 -0.2404 0.01041 0.00303 -0.0191 0.7077 0.1176
-3.250 -0.2165 0.01032 0.00288 -0.0182 0.6858 0.1288
-3.000 -0.1923 0.01022 0.00274 -0.0174 0.6658 0.1421
-2.750 -0.1681 0.01010 0.00261 -0.0166 0.6471 0.1592
-2.500 -0.1442 0.00995 0.00247 -0.0157 0.6301 0.1831
-2.250 -0.1243 0.00948 0.00226 -0.0142 0.6146 0.2644
-2.000 -0.1058 0.00895 0.00212 -0.0125 0.6004 0.3859
-1.500 -0.0605 0.00855 0.00196 -0.0102 0.5732 0.4870
-1.250 -0.0374 0.00840 0.00191 -0.0092 0.5608 0.5293
-1.000 -0.0145 0.00827 0.00187 -0.0080 0.5485 0.5713
-0.750 0.0087 0.00816 0.00183 -0.0069 0.5366 0.6077
-0.500 0.0318 0.00805 0.00182 -0.0058 0.5248 0.6486
-0.250 0.0549 0.00796 0.00182 -0.0046 0.5133 0.6872
0.000 0.0789 0.00792 0.00183 -0.0036 0.5021 0.7185
0.250 0.1032 0.00790 0.00186 -0.0027 0.4907 0.7499
0.500 0.1280 0.00789 0.00189 -0.0019 0.4793 0.7771
0.750 0.1533 0.00790 0.00192 -0.0011 0.4679 0.8018
1.250 0.2054 0.00795 0.00202 -0.0001 0.4446 0.8479
1.500 0.2328 0.00801 0.00206 0.0001 0.4329 0.8620
1.750 0.2611 0.00809 0.00211 0.0001 0.4205 0.8738
2.000 0.2897 0.00818 0.00217 0.0000 0.4081 0.8854
2.250 0.3188 0.00827 0.00223 -0.0003 0.3958 0.8972
2.500 0.3502 0.00837 0.00230 -0.0010 0.3840 0.9084
2.750 0.3834 0.00849 0.00239 -0.0023 0.3719 0.9187
3.000 0.4174 0.00863 0.00248 -0.0037 0.3600 0.9295
3.250 0.4569 0.00877 0.00259 -0.0064 0.3482 0.9387
3.500 0.4974 0.00894 0.00273 -0.0093 0.3365 0.9458
3.750 0.5385 0.00913 0.00286 -0.0124 0.3246 0.9507
4.000 0.5752 0.00931 0.00301 -0.0145 0.3141 0.9561
4.250 0.6136 0.00950 0.00317 -0.0170 0.3025 0.9590
4.500 0.6500 0.00971 0.00334 -0.0190 0.2915 0.9623
4.750 0.6844 0.00993 0.00352 -0.0205 0.2814 0.9665
5.000 0.7192 0.01013 0.00371 -0.0222 0.2714 0.9702
5.250 0.7535 0.01036 0.00391 -0.0237 0.2611 0.9742
5.500 0.7856 0.01062 0.00413 -0.0248 0.2498 0.9794
5.750 0.8157 0.01087 0.00435 -0.0255 0.2391 0.9869
6.000 0.8443 0.01114 0.00461 -0.0259 0.2301 0.9952
6.250 0.8769 0.01140 0.00483 -0.0272 0.2201 0.9979
6.500 0.9101 0.01165 0.00507 -0.0286 0.2105 0.9997
6.750 0.9335 0.01188 0.00528 -0.0279 0.2024 1.0000
7.000 0.9541 0.01214 0.00551 -0.0266 0.1928 1.0000
7.250 0.9749 0.01243 0.00576 -0.0254 0.1813 1.0000
7.500 0.9957 0.01275 0.00603 -0.0242 0.1698 1.0000
7.750 1.0165 0.01308 0.00632 -0.0230 0.1599 1.0000
8.000 1.0375 0.01342 0.00663 -0.0219 0.1506 1.0000
8.250 1.0590 0.01373 0.00694 -0.0208 0.1433 1.0000
8.500 1.0801 0.01408 0.00728 -0.0197 0.1363 1.0000
8.750 1.1014 0.01442 0.00761 -0.0186 0.1293 1.0000
9.000 1.1214 0.01485 0.00801 -0.0174 0.1199 1.0000
9.250 1.1416 0.01526 0.00840 -0.0162 0.1103 1.0000
9.500 1.1612 0.01571 0.00883 -0.0149 0.1002 1.0000
9.750 1.1783 0.01633 0.00936 -0.0133 0.0848 1.0000
10.000 1.1875 0.01746 0.01026 -0.0106 0.0511 1.0000
10.250 1.1925 0.01882 0.01146 -0.0073 0.0261 1.0000
10.500 1.2058 0.01957 0.01222 -0.0051 0.0214 1.0000
10.750 1.2200 0.02024 0.01292 -0.0031 0.0191 1.0000
11.000 1.2326 0.02095 0.01367 -0.0009 0.0174 1.0000
11.250 1.2408 0.02166 0.01444 0.0021 0.0162 1.0000
11.500 1.2498 0.02233 0.01518 0.0049 0.0154 1.0000
11.750 1.2582 0.02311 0.01602 0.0076 0.0146 1.0000
12.000 1.2653 0.02405 0.01701 0.0101 0.0138 1.0000
12.250 1.2711 0.02516 0.01820 0.0124 0.0133 1.0000
12.500 1.2773 0.02637 0.01948 0.0144 0.0129 1.0000
12.750 1.2841 0.02762 0.02082 0.0161 0.0125 1.0000
13.000 1.2899 0.02906 0.02235 0.0175 0.0122 1.0000
13.250 1.2944 0.03072 0.02411 0.0187 0.0118 1.0000
13.500 1.2979 0.03262 0.02610 0.0196 0.0116 1.0000
13.750 1.3004 0.03476 0.02834 0.0202 0.0113 1.0000
14.000 1.3011 0.03726 0.03093 0.0204 0.0110 1.0000
14.250 1.2999 0.04012 0.03390 0.0203 0.0109 1.0000
14.500 1.2970 0.04334 0.03723 0.0199 0.0107 1.0000
14.750 1.2912 0.04706 0.04105 0.0191 0.0105 1.0000
15.000 1.2829 0.05121 0.04532 0.0181 0.0104 1.0000
15.250 1.2714 0.05591 0.05014 0.0167 0.0102 1.0000
15.500 1.2609 0.06053 0.05489 0.0154 0.0102 1.0000
15.750 1.2498 0.06536 0.05984 0.0138 0.0101 1.0000
16.000 1.2387 0.07029 0.06490 0.0122 0.0100 1.0000
16.250 1.2269 0.07545 0.07017 0.0104 0.0099 1.0000
16.500 1.2135 0.08097 0.07581 0.0084 0.0099 1.0000
16.750 1.2006 0.08649 0.08145 0.0063 0.0098 1.0000
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Polar data table (+)
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