Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Supermarine 371-I (root) (supermarine371i-il) Reynolds number: 500,000 Max Cl/Cd: 63.97 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-supermarine371i-il-500000-n5.txt Download as CSV file: xf-supermarine371i-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-I (root)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9268 0.07648 0.07335 -0.0457 1.0000 0.0103
-15.750 -0.9559 0.06707 0.06372 -0.0517 1.0000 0.0103
-15.500 -0.9788 0.05976 0.05619 -0.0559 1.0000 0.0102
-15.250 -0.9938 0.05445 0.05071 -0.0584 1.0000 0.0102
-15.000 -0.9897 0.05211 0.04833 -0.0595 1.0000 0.0105
-14.750 -1.0013 0.04801 0.04407 -0.0606 1.0000 0.0106
-14.500 -1.0049 0.04510 0.04104 -0.0610 1.0000 0.0107
-14.250 -1.0049 0.04275 0.03860 -0.0611 1.0000 0.0109
-14.000 -1.0111 0.03982 0.03551 -0.0607 1.0000 0.0109
-13.750 -1.0077 0.03803 0.03363 -0.0602 1.0000 0.0111
-13.500 -1.0069 0.03602 0.03148 -0.0594 1.0000 0.0113
-13.250 -1.0040 0.03427 0.02961 -0.0584 1.0000 0.0115
-13.000 -1.0004 0.03261 0.02782 -0.0572 1.0000 0.0117
-12.750 -0.9960 0.03103 0.02610 -0.0558 1.0000 0.0119
-12.500 -0.9911 0.02949 0.02441 -0.0542 1.0000 0.0121
-12.250 -0.9832 0.02827 0.02306 -0.0527 1.0000 0.0124
-12.000 -0.9658 0.02690 0.02153 -0.0531 0.9621 0.0126
-11.750 -0.9338 0.02552 0.01993 -0.0562 0.9346 0.0128
-11.500 -0.9193 0.02422 0.01844 -0.0556 0.9085 0.0132
-11.250 -0.9097 0.02329 0.01737 -0.0535 0.8899 0.0135
-11.000 -0.8990 0.02249 0.01645 -0.0514 0.8765 0.0137
-10.750 -0.8857 0.02193 0.01579 -0.0496 0.8660 0.0141
-10.500 -0.8722 0.02134 0.01509 -0.0476 0.8568 0.0145
-10.250 -0.8585 0.02069 0.01433 -0.0457 0.8487 0.0147
-10.000 -0.8441 0.02010 0.01364 -0.0438 0.8416 0.0151
-9.750 -0.8277 0.01948 0.01292 -0.0423 0.8353 0.0155
-9.500 -0.8102 0.01886 0.01220 -0.0409 0.8293 0.0159
-9.250 -0.7919 0.01830 0.01153 -0.0396 0.8241 0.0162
-9.000 -0.7721 0.01780 0.01093 -0.0386 0.8188 0.0166
-8.750 -0.7536 0.01718 0.01023 -0.0373 0.8137 0.0171
-8.500 -0.7348 0.01659 0.00957 -0.0361 0.8091 0.0177
-8.250 -0.7140 0.01610 0.00904 -0.0352 0.8047 0.0183
-8.000 -0.6925 0.01566 0.00854 -0.0343 0.8005 0.0189
-7.750 -0.6708 0.01524 0.00805 -0.0335 0.7968 0.0196
-7.500 -0.6487 0.01484 0.00758 -0.0327 0.7935 0.0203
-7.250 -0.6259 0.01446 0.00714 -0.0320 0.7900 0.0211
-7.000 -0.6032 0.01406 0.00670 -0.0313 0.7865 0.0220
-6.750 -0.5803 0.01368 0.00628 -0.0306 0.7833 0.0236
-6.500 -0.5565 0.01338 0.00596 -0.0301 0.7805 0.0256
-6.250 -0.5322 0.01311 0.00564 -0.0296 0.7779 0.0275
-6.000 -0.5083 0.01277 0.00531 -0.0291 0.7749 0.0303
-5.750 -0.4836 0.01251 0.00502 -0.0287 0.7719 0.0334
-5.500 -0.4588 0.01226 0.00474 -0.0283 0.7690 0.0367
-5.250 -0.4342 0.01199 0.00445 -0.0279 0.7664 0.0409
-5.000 -0.4087 0.01180 0.00420 -0.0276 0.7642 0.0443
-4.750 -0.3839 0.01152 0.00392 -0.0272 0.7620 0.0501
-4.500 -0.3593 0.01122 0.00367 -0.0268 0.7596 0.0610
-4.250 -0.3339 0.01099 0.00359 -0.0265 0.7573 0.0945
-4.000 -0.3073 0.01087 0.00346 -0.0264 0.7551 0.1020
-3.750 -0.2808 0.01073 0.00332 -0.0263 0.7530 0.1076
-3.500 -0.2538 0.01065 0.00319 -0.0262 0.7510 0.1108
-3.250 -0.2273 0.01053 0.00304 -0.0261 0.7491 0.1135
-3.000 -0.2009 0.01037 0.00289 -0.0260 0.7471 0.1177
-2.750 -0.1741 0.01024 0.00277 -0.0259 0.7450 0.1210
-2.500 -0.1470 0.01014 0.00266 -0.0259 0.7431 0.1230
-2.250 -0.1198 0.01005 0.00257 -0.0259 0.7412 0.1251
-2.000 -0.0927 0.00995 0.00247 -0.0259 0.7393 0.1293
-1.750 -0.0658 0.00984 0.00239 -0.0258 0.7376 0.1348
-1.500 -0.0390 0.00970 0.00230 -0.0257 0.7359 0.1459
-1.250 -0.0176 0.00908 0.00212 -0.0249 0.7341 0.2697
-1.000 0.0036 0.00846 0.00195 -0.0241 0.7323 0.3964
-0.750 0.0246 0.00785 0.00181 -0.0232 0.7305 0.5186
-0.500 0.0462 0.00746 0.00188 -0.0220 0.7286 0.6359
-0.250 0.0735 0.00744 0.00192 -0.0220 0.7268 0.6615
0.000 0.1011 0.00742 0.00194 -0.0219 0.7240 0.6770
0.250 0.1288 0.00741 0.00195 -0.0219 0.7208 0.6886
0.500 0.1569 0.00743 0.00195 -0.0219 0.7178 0.6984
0.750 0.1844 0.00740 0.00199 -0.0219 0.7131 0.7069
1.000 0.2122 0.00739 0.00199 -0.0219 0.7071 0.7145
1.250 0.2402 0.00740 0.00198 -0.0219 0.7024 0.7190
1.500 0.2681 0.00739 0.00203 -0.0219 0.6975 0.7241
2.000 0.3235 0.00739 0.00206 -0.0219 0.6845 0.7353
2.250 0.3512 0.00739 0.00209 -0.0218 0.6767 0.7411
2.500 0.3786 0.00739 0.00211 -0.0217 0.6665 0.7462
2.750 0.4057 0.00739 0.00213 -0.0216 0.6545 0.7506
3.000 0.4331 0.00741 0.00218 -0.0215 0.6438 0.7551
3.250 0.4598 0.00744 0.00220 -0.0213 0.6236 0.7596
3.500 0.4836 0.00756 0.00220 -0.0204 0.5735 0.7646
3.750 0.5020 0.00805 0.00236 -0.0187 0.4961 0.7695
4.000 0.5204 0.00862 0.00266 -0.0172 0.4277 0.7739
4.250 0.5397 0.00916 0.00295 -0.0159 0.3672 0.7778
4.500 0.5591 0.00966 0.00325 -0.0146 0.3128 0.7815
4.750 0.5779 0.01020 0.00357 -0.0133 0.2567 0.7860
5.000 0.5973 0.01070 0.00387 -0.0120 0.2103 0.7910
5.250 0.6169 0.01115 0.00418 -0.0108 0.1722 0.7955
5.500 0.6360 0.01162 0.00450 -0.0095 0.1353 0.8014
5.750 0.6558 0.01203 0.00482 -0.0083 0.1107 0.8090
6.000 0.6763 0.01235 0.00512 -0.0071 0.0949 0.8177
6.250 0.6968 0.01268 0.00543 -0.0060 0.0812 0.8256
6.500 0.7168 0.01302 0.00575 -0.0048 0.0688 0.8321
7.000 0.7556 0.01370 0.00643 -0.0022 0.0510 0.8466
7.250 0.7747 0.01403 0.00678 -0.0009 0.0446 0.8552
7.500 0.7919 0.01434 0.00713 0.0009 0.0396 0.8656
7.750 0.8078 0.01467 0.00750 0.0029 0.0352 0.8776
8.000 0.8236 0.01503 0.00793 0.0048 0.0317 0.8929
8.250 0.8412 0.01540 0.00839 0.0064 0.0289 0.9126
8.500 0.8658 0.01595 0.00898 0.0062 0.0255 0.9372
8.750 0.9033 0.01652 0.00964 0.0033 0.0236 0.9612
9.000 0.9339 0.01714 0.01030 0.0017 0.0218 1.0000
9.250 0.9480 0.01772 0.01088 0.0035 0.0206 1.0000
9.500 0.9618 0.01836 0.01156 0.0053 0.0196 1.0000
9.750 0.9778 0.01889 0.01213 0.0067 0.0187 1.0000
10.000 0.9927 0.01952 0.01281 0.0082 0.0178 1.0000
10.250 1.0074 0.02018 0.01353 0.0097 0.0173 1.0000
10.500 1.0220 0.02087 0.01425 0.0110 0.0166 1.0000
10.750 1.0357 0.02164 0.01505 0.0124 0.0159 1.0000
11.000 1.0460 0.02267 0.01612 0.0142 0.0152 1.0000
11.250 1.0608 0.02340 0.01693 0.0153 0.0148 1.0000
11.500 1.0747 0.02421 0.01780 0.0166 0.0143 1.0000
11.750 1.0874 0.02512 0.01878 0.0178 0.0138 1.0000
12.000 1.0999 0.02606 0.01980 0.0190 0.0134 1.0000
12.250 1.1113 0.02710 0.02091 0.0203 0.0130 1.0000
12.500 1.1228 0.02815 0.02201 0.0214 0.0126 1.0000
12.750 1.1335 0.02926 0.02318 0.0225 0.0122 1.0000
13.000 1.1405 0.03070 0.02469 0.0238 0.0119 1.0000
13.250 1.1456 0.03233 0.02640 0.0252 0.0115 1.0000
13.500 1.1563 0.03353 0.02769 0.0261 0.0112 1.0000
13.750 1.1633 0.03506 0.02934 0.0271 0.0110 1.0000
14.000 1.1721 0.03645 0.03084 0.0279 0.0107 1.0000
14.250 1.1785 0.03808 0.03257 0.0287 0.0104 1.0000
14.500 1.1834 0.03989 0.03448 0.0295 0.0101 1.0000
14.750 1.1883 0.04173 0.03641 0.0301 0.0099 1.0000
15.000 1.1914 0.04379 0.03858 0.0307 0.0096 1.0000
15.250 1.1953 0.04586 0.04074 0.0310 0.0094 1.0000
15.500 1.1964 0.04830 0.04328 0.0312 0.0093 1.0000
15.750 1.1957 0.05103 0.04611 0.0312 0.0091 1.0000
16.000 1.1938 0.05404 0.04923 0.0310 0.0090 1.0000
16.250 1.1882 0.05764 0.05295 0.0304 0.0088 1.0000
16.500 1.1804 0.06173 0.05716 0.0295 0.0087 1.0000
16.750 1.1725 0.06610 0.06166 0.0281 0.0086 1.0000
17.000 1.1635 0.07090 0.06662 0.0263 0.0086 1.0000
17.250 1.1562 0.07572 0.07161 0.0242 0.0084 1.0000
17.500 1.1450 0.08136 0.07741 0.0215 0.0084 1.0000
17.750 1.1318 0.08763 0.08383 0.0183 0.0083 1.0000
18.000 1.1165 0.09452 0.09089 0.0147 0.0083 1.0000
18.250 1.0970 0.10240 0.09893 0.0104 0.0083 1.0000
18.500 1.0765 0.11083 0.10752 0.0057 0.0082 1.0000
18.750 1.0531 0.11996 0.11678 0.0006 0.0083 1.0000
19.000 1.0306 0.12936 0.12634 -0.0048 0.0083 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Supermarine 371-I (root) (supermarine371i-il)