Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 100,000 Max Cl/Cd: 37.54 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-100000-n5.txt Download as CSV file: xf-supermarine371ii-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-II (tip)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4395 0.08901 0.08453 -0.0219 1.0000 0.0173
-9.000 -0.5281 0.09404 0.08925 -0.0202 1.0000 0.0182
-8.750 -0.5288 0.08954 0.08482 -0.0227 1.0000 0.0175
-8.500 -0.5297 0.08519 0.08052 -0.0256 1.0000 0.0166
-8.250 -0.5340 0.08045 0.07583 -0.0295 1.0000 0.0163
-8.000 -0.5400 0.07636 0.07177 -0.0319 1.0000 0.0158
-7.750 -0.5443 0.07224 0.06763 -0.0336 1.0000 0.0153
-7.500 -0.5457 0.06808 0.06341 -0.0348 1.0000 0.0147
-7.250 -0.5455 0.06388 0.05913 -0.0355 1.0000 0.0141
-7.000 -0.5439 0.05977 0.05490 -0.0355 1.0000 0.0137
-6.750 -0.5413 0.05597 0.05096 -0.0347 1.0000 0.0131
-6.500 -0.5414 0.05254 0.04735 -0.0324 1.0000 0.0124
-6.250 -0.5402 0.04927 0.04388 -0.0300 0.9977 0.0122
-6.000 -0.5167 0.04425 0.03842 -0.0316 0.9875 0.0118
-5.750 -0.4925 0.04015 0.03389 -0.0330 0.9794 0.0120
-5.500 -0.4669 0.03788 0.03118 -0.0348 0.9728 0.0161
-5.250 -0.4376 0.03474 0.02746 -0.0353 0.9664 0.0196
-5.000 -0.4102 0.03142 0.02357 -0.0354 0.9601 0.0201
-4.750 -0.3813 0.02844 0.02005 -0.0356 0.9548 0.0203
-4.500 -0.3507 0.02582 0.01689 -0.0357 0.9505 0.0209
-4.250 -0.3225 0.02320 0.01391 -0.0355 0.9454 0.0218
-4.000 -0.2931 0.02099 0.01156 -0.0359 0.9415 0.0245
-3.750 -0.2631 0.02002 0.01036 -0.0363 0.9376 0.0334
-3.500 -0.2392 0.01854 0.00886 -0.0357 0.9319 0.0363
-3.250 -0.2128 0.01759 0.00777 -0.0355 0.9275 0.0400
-3.000 -0.1885 0.01685 0.00686 -0.0349 0.9223 0.0465
-2.750 -0.1643 0.01617 0.00616 -0.0343 0.9174 0.0693
-2.500 -0.1621 0.01328 0.00613 -0.0299 0.9127 0.6917
-2.250 -0.1503 0.01368 0.00663 -0.0242 0.9074 0.8244
-2.000 -0.1153 0.01455 0.00744 -0.0213 0.9073 0.9045
-1.750 -0.0800 0.01459 0.00724 -0.0228 0.9045 0.9158
-1.500 -0.0471 0.01452 0.00698 -0.0242 0.9015 0.9202
-1.250 -0.0193 0.01448 0.00679 -0.0247 0.8978 0.9260
-1.000 0.0132 0.01446 0.00665 -0.0261 0.8943 0.9296
-0.750 0.0442 0.01445 0.00650 -0.0273 0.8911 0.9343
-0.500 0.0741 0.01444 0.00641 -0.0282 0.8883 0.9394
-0.250 0.1090 0.01443 0.00634 -0.0301 0.8860 0.9426
0.000 0.1387 0.01448 0.00638 -0.0311 0.8820 0.9479
0.250 0.1691 0.01453 0.00642 -0.0323 0.8789 0.9532
0.500 0.2042 0.01457 0.00649 -0.0343 0.8764 0.9567
0.750 0.2375 0.01460 0.00656 -0.0360 0.8741 0.9611
1.000 0.2697 0.01469 0.00670 -0.0375 0.8712 0.9662
1.250 0.3030 0.01479 0.00690 -0.0394 0.8679 0.9712
1.500 0.3351 0.01489 0.00712 -0.0409 0.8647 0.9767
1.750 0.3697 0.01497 0.00734 -0.0428 0.8622 0.9813
2.000 0.4032 0.01506 0.00774 -0.0445 0.8599 0.9865
2.250 0.4357 0.01525 0.00816 -0.0463 0.8558 0.9929
2.500 0.4677 0.01502 0.00814 -0.0466 0.8430 0.9983
2.750 0.4803 0.01371 0.00678 -0.0397 0.7889 1.0000
3.000 0.4888 0.01302 0.00602 -0.0339 0.7269 1.0000
3.250 0.4825 0.01366 0.00506 -0.0257 0.3688 1.0000
3.500 0.4793 0.01605 0.00588 -0.0214 0.0808 1.0000
3.750 0.4940 0.01688 0.00661 -0.0191 0.0561 1.0000
4.000 0.5105 0.01765 0.00745 -0.0171 0.0477 1.0000
4.250 0.5270 0.01858 0.00850 -0.0151 0.0437 1.0000
4.500 0.5449 0.01949 0.00950 -0.0134 0.0381 1.0000
4.750 0.5634 0.02066 0.01093 -0.0119 0.0306 1.0000
5.000 0.5842 0.02225 0.01259 -0.0105 0.0267 1.0000
5.250 0.6082 0.02510 0.01544 -0.0096 0.0241 1.0000
5.500 0.6338 0.02657 0.01734 -0.0085 0.0204 1.0000
5.750 0.6546 0.02776 0.01871 -0.0078 0.0152 1.0000
6.000 0.6762 0.03063 0.02191 -0.0067 0.0143 1.0000
6.250 0.6947 0.03432 0.02605 -0.0053 0.0139 1.0000
6.500 0.7107 0.03793 0.03009 -0.0035 0.0137 1.0000
6.750 0.7248 0.04135 0.03396 -0.0018 0.0136 1.0000
7.000 0.7359 0.04503 0.03803 0.0000 0.0137 1.0000
7.250 0.7464 0.04844 0.04184 0.0017 0.0138 1.0000
7.500 0.7550 0.05181 0.04553 0.0034 0.0140 1.0000
7.750 0.7632 0.05501 0.04906 0.0052 0.0143 1.0000
8.000 0.7692 0.05871 0.05309 0.0070 0.0149 1.0000
8.250 0.7664 0.06367 0.05840 0.0088 0.0158 1.0000
8.500 0.7597 0.06828 0.06324 0.0100 0.0166 1.0000
8.750 0.7488 0.07240 0.06749 0.0110 0.0171 1.0000
9.000 0.7353 0.07640 0.07158 0.0113 0.0175 1.0000
9.250 0.7220 0.08094 0.07618 0.0099 0.0178 1.0000
9.500 0.7100 0.08628 0.08155 0.0069 0.0183 1.0000
9.750 0.7008 0.09243 0.08770 0.0026 0.0186 1.0000
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Polar data table (+)
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