Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 1,000,000 Max Cl/Cd: 58.68 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-1000000-n5.txt Download as CSV file: xf-supermarine371ii-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5738 0.14548 0.14381 0.0071 1.0000 0.0040
-8.000 -0.5712 0.06412 0.06210 -0.0359 0.8461 0.0017
-7.750 -0.5728 0.05978 0.05763 -0.0364 0.8356 0.0017
-7.500 -0.5735 0.05482 0.05251 -0.0365 0.8272 0.0016
-7.250 -0.5685 0.05042 0.04794 -0.0362 0.8204 0.0016
-7.000 -0.5635 0.04493 0.04222 -0.0354 0.8143 0.0016
-6.750 -0.5537 0.04025 0.03729 -0.0343 0.8089 0.0015
-6.500 -0.5436 0.03454 0.03125 -0.0326 0.8043 0.0015
-6.250 -0.5342 0.02706 0.02323 -0.0296 0.7996 0.0015
-6.000 -0.5268 0.01590 0.01091 -0.0248 0.7955 0.0017
-5.750 -0.5028 0.01448 0.00923 -0.0242 0.7920 0.0018
-5.500 -0.4804 0.01250 0.00694 -0.0233 0.7885 0.0022
-5.250 -0.4549 0.01193 0.00628 -0.0230 0.7851 0.0025
-5.000 -0.4293 0.01145 0.00571 -0.0228 0.7819 0.0027
-4.750 -0.4040 0.01086 0.00498 -0.0225 0.7792 0.0030
-4.500 -0.3781 0.01042 0.00447 -0.0223 0.7763 0.0035
-4.250 -0.3513 0.01022 0.00425 -0.0224 0.7735 0.0040
-4.000 -0.3256 0.00974 0.00368 -0.0221 0.7707 0.0044
-3.750 -0.3012 0.00898 0.00281 -0.0215 0.7681 0.0072
-3.500 -0.2741 0.00884 0.00264 -0.0215 0.7658 0.0095
-3.250 -0.2461 0.00885 0.00268 -0.0218 0.7634 0.0109
-3.000 -0.2190 0.00868 0.00249 -0.0218 0.7610 0.0114
-2.750 -0.1928 0.00829 0.00196 -0.0216 0.7586 0.0124
-2.500 -0.1659 0.00805 0.00164 -0.0215 0.7562 0.0139
-2.250 -0.1387 0.00786 0.00140 -0.0215 0.7540 0.0168
-2.000 -0.1114 0.00771 0.00126 -0.0216 0.7518 0.0255
-1.750 -0.0844 0.00749 0.00114 -0.0216 0.7497 0.0548
-1.500 -0.0579 0.00717 0.00101 -0.0216 0.7475 0.1214
-1.250 -0.0336 0.00650 0.00086 -0.0215 0.7454 0.2905
-1.000 -0.0159 0.00505 0.00069 -0.0203 0.7432 0.6860
-0.750 0.0105 0.00489 0.00066 -0.0201 0.7414 0.7219
-0.500 0.0377 0.00484 0.00066 -0.0201 0.7396 0.7417
-0.250 0.0651 0.00482 0.00072 -0.0200 0.7379 0.7688
0.000 0.0932 0.00483 0.00074 -0.0202 0.7359 0.7807
0.250 0.1214 0.00483 0.00075 -0.0204 0.7339 0.7864
0.500 0.1499 0.00485 0.00076 -0.0207 0.7320 0.7905
0.750 0.1782 0.00486 0.00077 -0.0209 0.7292 0.7939
1.000 0.2061 0.00487 0.00078 -0.0210 0.7246 0.7969
1.250 0.2343 0.00487 0.00081 -0.0212 0.7186 0.8003
1.500 0.2616 0.00489 0.00078 -0.0212 0.6989 0.8037
1.750 0.2887 0.00496 0.00079 -0.0211 0.6676 0.8068
2.000 0.3050 0.00629 0.00107 -0.0195 0.3790 0.8102
2.250 0.3252 0.00735 0.00141 -0.0188 0.1753 0.8140
2.500 0.3500 0.00779 0.00159 -0.0186 0.1005 0.8176
2.750 0.3754 0.00814 0.00178 -0.0184 0.0508 0.8207
3.000 0.4013 0.00839 0.00199 -0.0183 0.0268 0.8239
3.250 0.4278 0.00858 0.00218 -0.0182 0.0198 0.8273
3.500 0.4539 0.00883 0.00247 -0.0180 0.0151 0.8308
4.000 0.5069 0.00913 0.00285 -0.0179 0.0121 0.8379
4.250 0.5324 0.00942 0.00315 -0.0177 0.0067 0.8421
4.500 0.5580 0.00969 0.00350 -0.0174 0.0053 0.8464
4.750 0.5831 0.01001 0.00389 -0.0171 0.0043 0.8514
5.000 0.6079 0.01036 0.00428 -0.0167 0.0035 0.8574
5.250 0.6282 0.01140 0.00553 -0.0153 0.0025 0.8644
5.500 0.6511 0.01204 0.00630 -0.0145 0.0024 0.8724
5.750 0.6728 0.01295 0.00737 -0.0135 0.0022 0.8810
6.000 0.6941 0.01420 0.00882 -0.0123 0.0022 0.8907
6.250 0.7155 0.01596 0.01084 -0.0110 0.0021 0.9019
6.500 0.7362 0.01839 0.01365 -0.0096 0.0021 0.9155
6.750 0.7543 0.02180 0.01753 -0.0076 0.0021 0.9336
7.000 0.7736 0.02649 0.02274 -0.0061 0.0021 0.9608
7.250 0.7970 0.03199 0.02868 -0.0059 0.0020 1.0000
7.500 0.8070 0.03680 0.03382 -0.0033 0.0019 1.0000
7.750 0.8154 0.04130 0.03858 -0.0010 0.0018 1.0000
8.000 0.8203 0.04607 0.04361 0.0013 0.0017 1.0000
8.250 0.8216 0.05095 0.04870 0.0035 0.0017 1.0000
8.500 0.8205 0.05553 0.05347 0.0053 0.0016 1.0000
8.750 0.8138 0.06028 0.05838 0.0071 0.0017 1.0000
9.000 0.8062 0.06449 0.06271 0.0085 0.0016 1.0000
9.250 0.7905 0.06805 0.06636 0.0106 0.0016 1.0000
9.500 0.7730 0.07184 0.07022 0.0112 0.0015 1.0000
9.750 0.7535 0.07693 0.07536 0.0095 0.0016 1.0000
10.000 0.7379 0.08292 0.08140 0.0054 0.0016 1.0000
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Polar data table (+)
Polar graphs
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