Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.75 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-1000000.txt Download as CSV file: xf-supermarine371ii-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5516 0.08282 0.08131 -0.0233 1.0000 0.0051
-8.750 -0.5582 0.07699 0.07551 -0.0287 1.0000 0.0050
-8.500 -0.5698 0.07249 0.07101 -0.0323 1.0000 0.0050
-8.250 -0.5797 0.06846 0.06695 -0.0332 1.0000 0.0050
-8.000 -0.5756 0.06330 0.06170 -0.0367 0.9723 0.0050
-7.750 -0.5619 0.05862 0.05684 -0.0408 0.9366 0.0052
-7.500 -0.5598 0.05530 0.05334 -0.0401 0.9113 0.0054
-7.250 -0.5553 0.05159 0.04944 -0.0394 0.8946 0.0054
-7.000 -0.5474 0.04821 0.04588 -0.0386 0.8820 0.0056
-6.750 -0.5371 0.04479 0.04227 -0.0378 0.8715 0.0060
-6.500 -0.5246 0.04122 0.03848 -0.0368 0.8625 0.0065
-6.250 -0.4960 0.03986 0.03699 -0.0358 0.8556 0.0084
-4.250 -0.3433 0.01319 0.00772 -0.0251 0.8160 0.0078
-4.000 -0.3181 0.01173 0.00609 -0.0243 0.8125 0.0081
-3.750 -0.2912 0.01145 0.00573 -0.0242 0.8092 0.0087
-3.500 -0.2708 0.00953 0.00364 -0.0228 0.8058 0.0112
-3.250 -0.2447 0.00912 0.00319 -0.0226 0.8025 0.0128
-3.000 -0.2180 0.00887 0.00290 -0.0225 0.7994 0.0153
-2.750 -0.1907 0.00877 0.00277 -0.0225 0.7966 0.0164
-2.500 -0.1656 0.00820 0.00203 -0.0220 0.7939 0.0184
-2.250 -0.1388 0.00788 0.00168 -0.0219 0.7914 0.0240
-2.000 -0.1127 0.00748 0.00144 -0.0218 0.7887 0.0780
-1.750 -0.0909 0.00643 0.00118 -0.0213 0.7861 0.3259
-1.500 -0.0727 0.00512 0.00099 -0.0202 0.7836 0.6713
-1.250 -0.0465 0.00498 0.00096 -0.0199 0.7812 0.7170
-1.000 -0.0206 0.00489 0.00104 -0.0195 0.7789 0.7658
-0.750 0.0066 0.00494 0.00111 -0.0193 0.7767 0.7925
-0.500 0.0342 0.00494 0.00112 -0.0194 0.7745 0.8037
-0.250 0.0617 0.00494 0.00114 -0.0193 0.7725 0.8146
0.000 0.0896 0.00495 0.00114 -0.0194 0.7706 0.8221
0.250 0.1176 0.00495 0.00115 -0.0196 0.7686 0.8267
0.500 0.1459 0.00498 0.00117 -0.0198 0.7667 0.8310
0.750 0.1741 0.00496 0.00119 -0.0201 0.7643 0.8353
1.000 0.2019 0.00493 0.00119 -0.0201 0.7599 0.8398
1.250 0.2297 0.00494 0.00119 -0.0202 0.7548 0.8446
1.500 0.2575 0.00490 0.00119 -0.0203 0.7480 0.8490
1.750 0.2843 0.00482 0.00112 -0.0200 0.7322 0.8536
2.000 0.3109 0.00479 0.00107 -0.0197 0.7052 0.8586
2.250 0.3377 0.00481 0.00107 -0.0195 0.6792 0.8632
2.500 0.3636 0.00493 0.00109 -0.0192 0.6321 0.8683
2.750 0.3775 0.00654 0.00153 -0.0173 0.3198 0.8748
3.000 0.3943 0.00787 0.00199 -0.0160 0.0795 0.8814
3.500 0.4429 0.00872 0.00275 -0.0150 0.0193 0.8939
3.750 0.4688 0.00892 0.00299 -0.0147 0.0160 0.9009
4.000 0.4923 0.00939 0.00354 -0.0139 0.0124 0.9085
4.250 0.5133 0.01019 0.00451 -0.0126 0.0104 0.9181
4.500 0.5374 0.01053 0.00492 -0.0120 0.0091 0.9290
4.750 0.5601 0.01107 0.00559 -0.0110 0.0083 0.9429
5.000 0.5857 0.01179 0.00640 -0.0108 0.0077 0.9594
5.250 0.6181 0.01237 0.00703 -0.0122 0.0068 0.9734
5.500 0.6479 0.01510 0.00999 -0.0129 0.0054 0.9866
5.750 0.6799 0.01723 0.01238 -0.0137 0.0051 1.0000
6.000 0.6975 0.02519 0.02113 -0.0092 0.0088 1.0000
6.250 0.7166 0.02775 0.02393 -0.0076 0.0082 1.0000
6.500 0.7342 0.03042 0.02685 -0.0059 0.0077 1.0000
6.750 0.7501 0.03323 0.02988 -0.0042 0.0073 1.0000
7.000 0.7645 0.03594 0.03280 -0.0027 0.0069 1.0000
7.250 0.7769 0.03867 0.03574 -0.0012 0.0067 1.0000
7.500 0.7875 0.04160 0.03885 0.0004 0.0065 1.0000
7.750 0.7949 0.04462 0.04205 0.0020 0.0063 1.0000
8.000 0.7989 0.04825 0.04586 0.0038 0.0062 1.0000
8.250 0.7963 0.05248 0.05027 0.0058 0.0060 1.0000
8.500 0.7779 0.05864 0.05665 0.0083 0.0058 1.0000
8.750 0.7510 0.06506 0.06322 0.0110 0.0057 1.0000
9.000 0.7368 0.06819 0.06643 0.0132 0.0057 1.0000
9.250 0.7217 0.07204 0.07035 0.0136 0.0057 1.0000
9.500 0.7086 0.07643 0.07481 0.0123 0.0057 1.0000
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Polar data table (+)
Polar graphs
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