FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-100 AIRFOIL (fx60100-il) Reynolds number: 500,000 Max Cl/Cd: 109.8 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60100-il-500000.txt Download as CSV file: xf-fx60100-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-100 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2879 0.08431 0.08223 -0.0408 1.0000 0.0195
-9.250 -0.2935 0.08055 0.07851 -0.0409 1.0000 0.0195
-9.000 -0.3021 0.07732 0.07532 -0.0398 1.0000 0.0195
-8.750 -0.3151 0.07473 0.07279 -0.0377 1.0000 0.0195
-8.500 -0.3277 0.06558 0.06367 -0.0423 0.9983 0.0200
-8.250 -0.3177 0.06163 0.05973 -0.0451 0.9960 0.0207
-8.000 -0.3017 0.05900 0.05709 -0.0477 0.9937 0.0219
-7.750 -0.2974 0.05280 0.05090 -0.0532 0.9893 0.0224
-7.500 -0.3612 0.05081 0.04841 -0.0817 0.9849 0.0195
-7.250 -0.3481 0.04027 0.03763 -0.0942 0.9782 0.0209
-7.000 -0.3180 0.03782 0.03510 -0.0987 0.9750 0.0222
-6.750 -0.2828 0.03391 0.03088 -0.1049 0.9725 0.0245
-6.500 -0.2437 0.02840 0.02463 -0.1126 0.9705 0.0286
-6.250 -0.2162 0.02634 0.02257 -0.1141 0.9654 0.0301
-6.000 -0.1835 0.02446 0.02050 -0.1164 0.9615 0.0329
-5.750 -0.1448 0.01755 0.01262 -0.1181 0.9583 0.0174
-5.500 -0.1113 0.01502 0.00964 -0.1186 0.9547 0.0142
-5.250 -0.0833 0.01381 0.00830 -0.1186 0.9484 0.0141
-5.000 -0.0528 0.01246 0.00685 -0.1193 0.9440 0.0144
-4.750 -0.0238 0.01154 0.00586 -0.1197 0.9387 0.0149
-4.500 0.0045 0.01092 0.00520 -0.1199 0.9326 0.0161
-4.250 0.0343 0.01040 0.00461 -0.1202 0.9279 0.0172
-4.000 0.0623 0.00992 0.00404 -0.1201 0.9210 0.0176
-3.750 0.0912 0.00952 0.00353 -0.1202 0.9150 0.0183
-3.500 0.1195 0.00923 0.00313 -0.1200 0.9080 0.0195
-3.250 0.1484 0.00872 0.00268 -0.1201 0.9012 0.0467
-3.000 0.1776 0.00763 0.00229 -0.1211 0.8946 0.2492
-2.750 0.2058 0.00728 0.00218 -0.1213 0.8874 0.3353
-2.500 0.2338 0.00713 0.00214 -0.1212 0.8799 0.3931
-2.250 0.2617 0.00705 0.00211 -0.1210 0.8721 0.4279
-2.000 0.2896 0.00702 0.00205 -0.1208 0.8639 0.4436
-1.750 0.3177 0.00699 0.00197 -0.1206 0.8560 0.4561
-1.500 0.3454 0.00696 0.00193 -0.1203 0.8460 0.4698
-1.250 0.3732 0.00695 0.00188 -0.1201 0.8361 0.4834
-1.000 0.4008 0.00694 0.00183 -0.1198 0.8244 0.4961
-0.750 0.4284 0.00694 0.00179 -0.1194 0.8122 0.5105
-0.500 0.4562 0.00694 0.00178 -0.1192 0.7999 0.5248
-0.250 0.4839 0.00693 0.00178 -0.1190 0.7876 0.5365
0.000 0.5117 0.00695 0.00178 -0.1188 0.7749 0.5488
0.250 0.5393 0.00697 0.00179 -0.1185 0.7606 0.5623
0.500 0.5665 0.00701 0.00179 -0.1182 0.7428 0.5753
0.750 0.5937 0.00707 0.00180 -0.1179 0.7231 0.5867
1.000 0.6208 0.00715 0.00183 -0.1175 0.7012 0.5982
1.250 0.6477 0.00724 0.00186 -0.1172 0.6798 0.6096
1.500 0.6748 0.00733 0.00192 -0.1169 0.6593 0.6213
1.750 0.7016 0.00744 0.00199 -0.1166 0.6390 0.6338
2.000 0.7286 0.00755 0.00209 -0.1163 0.6179 0.6474
2.500 0.7816 0.00785 0.00230 -0.1157 0.5723 0.6769
2.750 0.8079 0.00801 0.00243 -0.1153 0.5500 0.6936
3.000 0.8342 0.00817 0.00259 -0.1150 0.5274 0.7131
3.250 0.8603 0.00831 0.00275 -0.1146 0.5057 0.7376
3.500 0.8859 0.00844 0.00292 -0.1141 0.4829 0.7723
3.750 0.9093 0.00847 0.00309 -0.1131 0.4613 0.8362
4.000 0.9300 0.00847 0.00319 -0.1114 0.4364 1.0000
4.250 0.9561 0.00878 0.00339 -0.1112 0.4094 1.0000
4.500 0.9817 0.00915 0.00362 -0.1108 0.3777 1.0000
4.750 1.0065 0.00958 0.00388 -0.1104 0.3412 1.0000
5.000 1.0310 0.01007 0.00419 -0.1099 0.3009 1.0000
5.250 1.0552 0.01058 0.00453 -0.1095 0.2649 1.0000
5.500 1.0792 0.01112 0.00489 -0.1090 0.2284 1.0000
5.750 1.1028 0.01170 0.00529 -0.1084 0.1923 1.0000
6.000 1.1263 0.01229 0.00574 -0.1078 0.1632 1.0000
6.250 1.1497 0.01287 0.00618 -0.1073 0.1371 1.0000
6.500 1.1737 0.01337 0.00663 -0.1067 0.1213 1.0000
6.750 1.1975 0.01387 0.00707 -0.1062 0.1046 1.0000
7.000 1.2206 0.01444 0.00757 -0.1055 0.0915 1.0000
7.250 1.2441 0.01494 0.00808 -0.1049 0.0802 1.0000
7.500 1.2671 0.01549 0.00857 -0.1042 0.0680 1.0000
7.750 1.2893 0.01610 0.00913 -0.1035 0.0587 1.0000
8.000 1.3096 0.01690 0.00989 -0.1024 0.0514 1.0000
8.250 1.3329 0.01734 0.01041 -0.1017 0.0482 1.0000
8.500 1.3552 0.01786 0.01100 -0.1009 0.0442 1.0000
8.750 1.3747 0.01865 0.01180 -0.0998 0.0398 1.0000
9.000 1.3976 0.01903 0.01225 -0.0991 0.0378 1.0000
9.250 1.4197 0.01947 0.01269 -0.0984 0.0344 1.0000
9.500 1.4395 0.02011 0.01331 -0.0974 0.0299 1.0000
9.750 1.4613 0.02051 0.01374 -0.0966 0.0256 1.0000
10.000 1.4801 0.02118 0.01440 -0.0954 0.0190 1.0000
10.250 1.4927 0.02239 0.01550 -0.0934 0.0092 1.0000
10.500 1.5044 0.02354 0.01670 -0.0911 0.0070 1.0000
10.750 1.5152 0.02454 0.01783 -0.0887 0.0063 1.0000
11.000 1.5239 0.02566 0.01906 -0.0861 0.0059 1.0000
11.250 1.5309 0.02693 0.02045 -0.0834 0.0055 1.0000
11.500 1.5352 0.02846 0.02211 -0.0806 0.0051 1.0000
11.750 1.5359 0.03031 0.02413 -0.0777 0.0049 1.0000
12.000 1.5390 0.03205 0.02600 -0.0753 0.0048 1.0000
12.250 1.5417 0.03390 0.02800 -0.0732 0.0047 1.0000
12.500 1.5427 0.03599 0.03023 -0.0713 0.0046 1.0000
12.750 1.5424 0.03833 0.03272 -0.0695 0.0046 1.0000
13.000 1.5404 0.04097 0.03551 -0.0681 0.0045 1.0000
13.250 1.5370 0.04391 0.03862 -0.0669 0.0045 1.0000
13.500 1.5325 0.04717 0.04205 -0.0662 0.0044 1.0000
13.750 1.5265 0.05081 0.04585 -0.0658 0.0044 1.0000
14.000 1.5193 0.05485 0.05005 -0.0660 0.0043 1.0000
14.250 1.5107 0.05930 0.05467 -0.0666 0.0043 1.0000
14.500 1.5013 0.06418 0.05971 -0.0677 0.0043 1.0000
14.750 1.4907 0.06954 0.06524 -0.0693 0.0043 1.0000
15.000 1.4791 0.07538 0.07125 -0.0714 0.0043 1.0000
15.250 1.4667 0.08165 0.07769 -0.0740 0.0043 1.0000
15.500 1.4535 0.08836 0.08457 -0.0770 0.0043 1.0000
15.750 1.4397 0.09546 0.09183 -0.0804 0.0043 1.0000
16.000 1.4255 0.10291 0.09945 -0.0842 0.0043 1.0000
16.250 1.4102 0.11080 0.10750 -0.0883 0.0043 1.0000
16.500 1.3954 0.11884 0.11569 -0.0927 0.0043 1.0000
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