S1048 14% (Danny Howell) (s1048-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1048 14% (Danny Howell) (s1048-il) Reynolds number: 100,000 Max Cl/Cd: 40.33 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1048-il-100000.txt Download as CSV file: xf-s1048-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S1048 14% (Danny Howell)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8750 0.09024 0.08483 -0.0253 1.0000 0.0457
-14.000 -0.9020 0.08353 0.07786 -0.0301 1.0000 0.0450
-13.750 -0.9245 0.07738 0.07153 -0.0333 1.0000 0.0449
-13.500 -0.9441 0.07188 0.06583 -0.0356 1.0000 0.0447
-13.250 -0.9614 0.06714 0.06089 -0.0372 1.0000 0.0446
-13.000 -0.9809 0.06290 0.05639 -0.0382 1.0000 0.0448
-12.750 -0.9967 0.05933 0.05256 -0.0382 1.0000 0.0449
-12.500 -1.0105 0.05612 0.04912 -0.0374 1.0000 0.0451
-12.250 -1.0069 0.05167 0.04459 -0.0371 1.0000 0.0468
-12.000 -1.0045 0.04899 0.04180 -0.0361 1.0000 0.0481
-11.750 -1.0035 0.04654 0.03916 -0.0347 1.0000 0.0496
-11.500 -0.9988 0.04402 0.03643 -0.0332 1.0000 0.0512
-11.250 -0.9918 0.04156 0.03372 -0.0316 1.0000 0.0531
-11.000 -0.9856 0.03954 0.03139 -0.0295 1.0000 0.0552
-10.750 -0.9663 0.03694 0.02894 -0.0292 1.0000 0.0602
-10.500 -0.9564 0.03522 0.02707 -0.0274 1.0000 0.0648
-10.250 -0.9417 0.03304 0.02495 -0.0261 1.0000 0.0710
-10.000 -0.9346 0.03159 0.02334 -0.0238 1.0000 0.0788
-9.750 -0.9266 0.02973 0.02164 -0.0217 1.0000 0.0897
-9.500 -0.9210 0.02798 0.01992 -0.0192 1.0000 0.1052
-9.250 -0.9177 0.02622 0.01841 -0.0165 1.0000 0.1253
-9.000 -0.9133 0.02469 0.01706 -0.0137 1.0000 0.1535
-8.750 -0.9060 0.02349 0.01598 -0.0112 1.0000 0.1845
-8.500 -0.8956 0.02261 0.01518 -0.0089 1.0000 0.2145
-8.250 -0.8830 0.02198 0.01461 -0.0068 1.0000 0.2422
-8.000 -0.8688 0.02154 0.01422 -0.0047 1.0000 0.2685
-7.750 -0.8533 0.02117 0.01382 -0.0027 1.0000 0.2931
-7.500 -0.8364 0.02086 0.01350 -0.0009 1.0000 0.3159
-7.250 -0.8186 0.02052 0.01315 0.0009 1.0000 0.3364
-7.000 -0.7996 0.02024 0.01292 0.0025 1.0000 0.3555
-6.750 -0.7810 0.01996 0.01261 0.0042 1.0000 0.3744
-6.500 -0.7630 0.01967 0.01223 0.0060 1.0000 0.3930
-6.250 -0.7438 0.01940 0.01198 0.0076 1.0000 0.4098
-6.000 -0.7247 0.01914 0.01175 0.0092 1.0000 0.4257
-5.750 -0.7065 0.01889 0.01151 0.0109 1.0000 0.4411
-5.500 -0.6892 0.01866 0.01128 0.0127 1.0000 0.4561
-5.250 -0.6729 0.01845 0.01105 0.0147 1.0000 0.4707
-5.000 -0.6575 0.01826 0.01084 0.0166 1.0000 0.4850
-4.750 -0.6427 0.01810 0.01066 0.0185 1.0000 0.4992
-4.500 -0.6273 0.01800 0.01059 0.0204 1.0000 0.5123
-4.250 -0.6119 0.01792 0.01053 0.0221 1.0000 0.5253
-4.000 -0.5963 0.01788 0.01051 0.0237 1.0000 0.5383
-3.750 -0.5544 0.01794 0.01053 0.0203 0.9906 0.5561
-3.500 -0.5065 0.01796 0.01049 0.0160 0.9783 0.5747
-3.250 -0.4588 0.01798 0.01054 0.0120 0.9664 0.5915
-3.000 -0.4095 0.01797 0.01053 0.0079 0.9554 0.6082
-2.750 -0.3646 0.01791 0.01048 0.0047 0.9428 0.6243
-2.500 -0.3190 0.01783 0.01042 0.0014 0.9309 0.6404
-2.250 -0.2744 0.01772 0.01032 -0.0015 0.9193 0.6563
-2.000 -0.2303 0.01758 0.01020 -0.0041 0.9080 0.6719
-1.750 -0.1916 0.01746 0.01008 -0.0056 0.8950 0.6870
-1.500 -0.1585 0.01735 0.00998 -0.0060 0.8803 0.7016
-1.250 -0.1282 0.01727 0.00990 -0.0058 0.8653 0.7161
-1.000 -0.1003 0.01720 0.00982 -0.0051 0.8501 0.7306
-0.750 -0.0740 0.01715 0.00977 -0.0040 0.8348 0.7451
-0.500 -0.0489 0.01711 0.00973 -0.0028 0.8196 0.7597
-0.250 -0.0243 0.01709 0.00971 -0.0014 0.8044 0.7745
0.000 0.0000 0.01708 0.00970 0.0000 0.7894 0.7894
0.250 0.0243 0.01709 0.00971 0.0014 0.7745 0.8044
0.500 0.0489 0.01711 0.00973 0.0028 0.7597 0.8196
0.750 0.0740 0.01715 0.00977 0.0040 0.7451 0.8348
1.000 0.1003 0.01720 0.00982 0.0051 0.7306 0.8501
1.250 0.1282 0.01727 0.00990 0.0058 0.7161 0.8653
1.500 0.1585 0.01735 0.00998 0.0060 0.7016 0.8803
1.750 0.1916 0.01746 0.01008 0.0056 0.6870 0.8950
2.000 0.2303 0.01759 0.01020 0.0041 0.6720 0.9080
2.250 0.2744 0.01772 0.01032 0.0015 0.6564 0.9193
2.500 0.3191 0.01783 0.01042 -0.0014 0.6404 0.9309
2.750 0.3646 0.01791 0.01049 -0.0047 0.6244 0.9428
3.000 0.4095 0.01797 0.01053 -0.0079 0.6082 0.9554
3.250 0.4587 0.01798 0.01053 -0.0120 0.5914 0.9664
3.500 0.5065 0.01796 0.01048 -0.0160 0.5747 0.9783
3.750 0.5544 0.01793 0.01053 -0.0203 0.5561 0.9906
4.000 0.5963 0.01788 0.01051 -0.0237 0.5384 1.0000
4.250 0.6119 0.01792 0.01053 -0.0221 0.5253 1.0000
4.500 0.6272 0.01799 0.01059 -0.0204 0.5123 1.0000
4.750 0.6427 0.01810 0.01066 -0.0185 0.4992 1.0000
5.000 0.6575 0.01826 0.01084 -0.0166 0.4850 1.0000
5.250 0.6729 0.01845 0.01104 -0.0147 0.4707 1.0000
5.500 0.6892 0.01866 0.01128 -0.0127 0.4561 1.0000
5.750 0.7065 0.01889 0.01151 -0.0109 0.4411 1.0000
6.000 0.7247 0.01914 0.01175 -0.0092 0.4257 1.0000
6.250 0.7438 0.01939 0.01198 -0.0076 0.4098 1.0000
6.500 0.7630 0.01967 0.01223 -0.0060 0.3930 1.0000
6.750 0.7810 0.01996 0.01261 -0.0042 0.3744 1.0000
7.000 0.7996 0.02024 0.01292 -0.0025 0.3555 1.0000
7.250 0.8186 0.02052 0.01315 -0.0009 0.3364 1.0000
7.500 0.8365 0.02086 0.01351 0.0009 0.3159 1.0000
7.750 0.8534 0.02117 0.01383 0.0027 0.2932 1.0000
8.000 0.8688 0.02154 0.01422 0.0047 0.2684 1.0000
8.250 0.8830 0.02198 0.01461 0.0068 0.2422 1.0000
8.500 0.8956 0.02262 0.01518 0.0089 0.2145 1.0000
8.750 0.9060 0.02348 0.01598 0.0112 0.1844 1.0000
9.000 0.9134 0.02469 0.01706 0.0137 0.1535 1.0000
9.250 0.9178 0.02622 0.01841 0.0165 0.1254 1.0000
9.500 0.9209 0.02799 0.01992 0.0192 0.1050 1.0000
9.750 0.9268 0.02973 0.02161 0.0217 0.0898 1.0000
10.000 0.9352 0.03160 0.02334 0.0237 0.0789 1.0000
10.250 0.9422 0.03305 0.02496 0.0261 0.0711 1.0000
10.500 0.9566 0.03522 0.02707 0.0274 0.0648 1.0000
10.750 0.9658 0.03692 0.02892 0.0293 0.0601 1.0000
11.000 0.9855 0.03954 0.03139 0.0295 0.0552 1.0000
11.250 0.9916 0.04158 0.03374 0.0316 0.0530 1.0000
11.500 0.9991 0.04404 0.03646 0.0332 0.0512 1.0000
11.750 1.0038 0.04654 0.03916 0.0347 0.0496 1.0000
12.000 1.0049 0.04913 0.04194 0.0361 0.0483 1.0000
12.250 1.0063 0.05171 0.04466 0.0371 0.0470 1.0000
12.500 1.0114 0.05573 0.04872 0.0374 0.0453 1.0000
12.750 0.9984 0.05941 0.05264 0.0381 0.0450 1.0000
13.000 0.9813 0.06294 0.05643 0.0381 0.0448 1.0000
13.250 0.9640 0.06715 0.06088 0.0373 0.0447 1.0000
13.500 0.9446 0.07201 0.06597 0.0356 0.0447 1.0000
13.750 0.9253 0.07738 0.07153 0.0332 0.0449 1.0000
14.000 0.9054 0.08332 0.07763 0.0303 0.0450 1.0000
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