Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-I (root) (supermarine371i-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.26 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371i-il-1000000.txt Download as CSV file: xf-supermarine371i-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7735 0.12304 0.12119 -0.0186 1.0000 0.0109
-16.500 -0.8473 0.10159 0.09955 -0.0301 1.0000 0.0105
-16.250 -0.9153 0.08266 0.08036 -0.0415 1.0000 0.0103
-16.000 -0.9506 0.07150 0.06901 -0.0488 1.0000 0.0103
-15.750 -0.9744 0.06345 0.06077 -0.0539 1.0000 0.0102
-15.500 -0.9917 0.05731 0.05447 -0.0574 1.0000 0.0103
-15.250 -1.0005 0.05298 0.05001 -0.0595 1.0000 0.0104
-15.000 -1.0126 0.04866 0.04553 -0.0609 1.0000 0.0105
-14.750 -1.0288 0.04428 0.04097 -0.0616 1.0000 0.0104
-14.500 -1.0283 0.04197 0.03854 -0.0617 1.0000 0.0105
-14.250 -1.0277 0.03980 0.03627 -0.0615 1.0000 0.0106
-14.000 -1.0285 0.03759 0.03393 -0.0610 1.0000 0.0107
-13.750 -1.0333 0.03506 0.03123 -0.0599 1.0000 0.0108
-13.500 -1.0514 0.03126 0.02718 -0.0578 1.0000 0.0111
-13.250 -1.0517 0.02931 0.02513 -0.0561 1.0000 0.0113
-13.000 -1.0468 0.02790 0.02363 -0.0546 1.0000 0.0114
-12.750 -1.0379 0.02693 0.02263 -0.0532 1.0000 0.0117
-12.500 -1.0279 0.02610 0.02175 -0.0517 1.0000 0.0119
-12.250 -1.0184 0.02519 0.02078 -0.0501 1.0000 0.0121
-12.000 -1.0096 0.02418 0.01967 -0.0481 1.0000 0.0123
-11.750 -0.9810 0.02300 0.01838 -0.0502 0.9659 0.0127
-11.500 -0.9461 0.02184 0.01704 -0.0534 0.9371 0.0130
-11.250 -0.9317 0.02134 0.01637 -0.0517 0.9084 0.0134
-11.000 -0.9210 0.02063 0.01551 -0.0492 0.8905 0.0135
-10.750 -0.9083 0.02011 0.01485 -0.0469 0.8775 0.0137
-10.500 -0.8939 0.01973 0.01435 -0.0449 0.8668 0.0139
-10.250 -0.8860 0.01822 0.01269 -0.0422 0.8575 0.0145
-10.000 -0.8716 0.01740 0.01177 -0.0403 0.8498 0.0148
-9.750 -0.8525 0.01694 0.01127 -0.0392 0.8429 0.0152
-9.500 -0.8334 0.01647 0.01072 -0.0380 0.8367 0.0156
-9.250 -0.8131 0.01600 0.01021 -0.0370 0.8310 0.0162
-9.000 -0.7933 0.01548 0.00960 -0.0358 0.8253 0.0165
-8.750 -0.7723 0.01507 0.00911 -0.0349 0.8201 0.0170
-8.500 -0.7506 0.01463 0.00862 -0.0340 0.8155 0.0174
-8.250 -0.7276 0.01432 0.00826 -0.0334 0.8109 0.0177
-8.000 -0.7107 0.01348 0.00732 -0.0317 0.8065 0.0186
-7.750 -0.6885 0.01307 0.00687 -0.0310 0.8026 0.0194
-7.500 -0.6651 0.01272 0.00650 -0.0304 0.7989 0.0202
-7.250 -0.6414 0.01240 0.00614 -0.0298 0.7953 0.0211
-7.000 -0.6175 0.01211 0.00579 -0.0292 0.7919 0.0218
-6.750 -0.5938 0.01180 0.00541 -0.0286 0.7884 0.0226
-6.500 -0.5707 0.01136 0.00497 -0.0279 0.7856 0.0247
-6.250 -0.5456 0.01111 0.00472 -0.0276 0.7826 0.0266
-6.000 -0.5205 0.01086 0.00444 -0.0272 0.7796 0.0288
-5.750 -0.4962 0.01055 0.00413 -0.0267 0.7767 0.0327
-5.500 -0.4704 0.01039 0.00393 -0.0264 0.7738 0.0356
-5.250 -0.4459 0.01007 0.00363 -0.0260 0.7714 0.0412
-5.000 -0.4196 0.00990 0.00343 -0.0258 0.7690 0.0444
-4.750 -0.3947 0.00959 0.00314 -0.0254 0.7666 0.0521
-4.500 -0.3704 0.00925 0.00294 -0.0250 0.7643 0.0766
-4.250 -0.3434 0.00913 0.00288 -0.0249 0.7621 0.0988
-4.000 -0.3157 0.00910 0.00281 -0.0250 0.7600 0.1033
-3.750 -0.2891 0.00898 0.00269 -0.0249 0.7577 0.1090
-3.500 -0.2617 0.00888 0.00260 -0.0249 0.7560 0.1133
-3.250 -0.2340 0.00881 0.00252 -0.0250 0.7540 0.1159
-3.000 -0.2070 0.00867 0.00239 -0.0250 0.7519 0.1199
-2.750 -0.1799 0.00854 0.00227 -0.0250 0.7500 0.1241
-2.500 -0.1525 0.00844 0.00217 -0.0250 0.7482 0.1266
-2.250 -0.1249 0.00836 0.00209 -0.0250 0.7464 0.1290
-2.000 -0.0973 0.00829 0.00201 -0.0251 0.7447 0.1335
-1.750 -0.0700 0.00820 0.00195 -0.0251 0.7428 0.1405
-1.500 -0.0452 0.00786 0.00184 -0.0248 0.7411 0.2032
-1.250 -0.0230 0.00727 0.00168 -0.0241 0.7394 0.3220
-1.000 -0.0017 0.00662 0.00152 -0.0232 0.7375 0.4568
-0.750 0.0178 0.00591 0.00143 -0.0218 0.7350 0.6250
-0.500 0.0454 0.00586 0.00143 -0.0218 0.7324 0.6567
-0.250 0.0734 0.00584 0.00143 -0.0218 0.7296 0.6724
0.000 0.1012 0.00585 0.00146 -0.0218 0.7260 0.6865
0.250 0.1290 0.00579 0.00146 -0.0218 0.7218 0.7000
0.500 0.1571 0.00578 0.00146 -0.0219 0.7178 0.7109
0.750 0.1854 0.00578 0.00148 -0.0219 0.7147 0.7195
1.000 0.2137 0.00581 0.00149 -0.0220 0.7104 0.7258
1.250 0.2418 0.00577 0.00151 -0.0221 0.7057 0.7318
1.500 0.2703 0.00577 0.00151 -0.0222 0.7018 0.7372
1.750 0.2986 0.00580 0.00152 -0.0223 0.6966 0.7414
2.000 0.3267 0.00575 0.00153 -0.0224 0.6903 0.7456
2.250 0.3548 0.00575 0.00153 -0.0224 0.6840 0.7499
2.500 0.3832 0.00577 0.00157 -0.0226 0.6788 0.7539
2.750 0.4113 0.00575 0.00158 -0.0226 0.6705 0.7575
3.000 0.4389 0.00574 0.00160 -0.0226 0.6604 0.7621
3.250 0.4666 0.00577 0.00163 -0.0226 0.6510 0.7662
3.500 0.4944 0.00580 0.00166 -0.0226 0.6365 0.7700
3.750 0.5213 0.00584 0.00170 -0.0225 0.6129 0.7738
4.000 0.5428 0.00616 0.00178 -0.0213 0.5403 0.7784
4.250 0.5606 0.00683 0.00209 -0.0196 0.4537 0.7836
4.500 0.5791 0.00744 0.00239 -0.0182 0.3743 0.7885
4.750 0.5974 0.00804 0.00270 -0.0167 0.3026 0.7936
5.000 0.6167 0.00858 0.00299 -0.0154 0.2418 0.7990
5.250 0.6368 0.00906 0.00327 -0.0142 0.1944 0.8038
5.750 0.6778 0.00989 0.00382 -0.0120 0.1250 0.8153
6.000 0.6991 0.01020 0.00409 -0.0110 0.1049 0.8234
6.250 0.7203 0.01053 0.00437 -0.0099 0.0872 0.8314
6.500 0.7410 0.01086 0.00465 -0.0088 0.0717 0.8387
6.750 0.7618 0.01118 0.00493 -0.0077 0.0597 0.8465
7.000 0.7823 0.01147 0.00523 -0.0066 0.0509 0.8548
7.500 0.8216 0.01209 0.00587 -0.0039 0.0365 0.8758
7.750 0.8390 0.01244 0.00624 -0.0022 0.0311 0.8895
8.000 0.8566 0.01271 0.00658 -0.0004 0.0281 0.9072
8.250 0.8725 0.01308 0.00704 0.0016 0.0250 0.9351
8.500 0.9092 0.01351 0.00756 -0.0009 0.0232 0.9613
8.750 0.9516 0.01421 0.00826 -0.0049 0.0208 0.9839
9.000 0.9714 0.01474 0.00883 -0.0040 0.0196 1.0000
9.250 0.9861 0.01512 0.00923 -0.0019 0.0190 1.0000
9.500 1.0008 0.01556 0.00970 0.0001 0.0181 1.0000
9.750 1.0158 0.01604 0.01020 0.0018 0.0173 1.0000
10.000 1.0285 0.01669 0.01087 0.0039 0.0166 1.0000
10.250 1.0366 0.01767 0.01191 0.0064 0.0158 1.0000
10.500 1.0540 0.01811 0.01239 0.0077 0.0154 1.0000
10.750 1.0693 0.01871 0.01303 0.0091 0.0150 1.0000
11.000 1.0848 0.01931 0.01368 0.0104 0.0145 1.0000
11.250 1.0991 0.02000 0.01441 0.0118 0.0140 1.0000
11.500 1.1131 0.02073 0.01517 0.0132 0.0136 1.0000
11.750 1.1253 0.02161 0.01609 0.0146 0.0130 1.0000
12.000 1.1323 0.02288 0.01742 0.0166 0.0126 1.0000
12.250 1.1392 0.02422 0.01885 0.0185 0.0122 1.0000
12.500 1.1535 0.02500 0.01969 0.0195 0.0120 1.0000
12.750 1.1653 0.02600 0.02076 0.0207 0.0118 1.0000
13.000 1.1777 0.02696 0.02179 0.0218 0.0115 1.0000
13.250 1.1880 0.02810 0.02300 0.0229 0.0112 1.0000
13.500 1.1979 0.02929 0.02427 0.0241 0.0110 1.0000
13.750 1.2098 0.03033 0.02535 0.0249 0.0106 1.0000
14.000 1.2197 0.03154 0.02661 0.0258 0.0103 1.0000
14.250 1.2269 0.03300 0.02812 0.0268 0.0101 1.0000
14.500 1.2295 0.03490 0.03009 0.0279 0.0098 1.0000
14.750 1.2272 0.03728 0.03259 0.0292 0.0096 1.0000
15.000 1.2190 0.04033 0.03579 0.0306 0.0094 1.0000
15.250 1.2251 0.04208 0.03764 0.0310 0.0093 1.0000
15.500 1.2315 0.04388 0.03953 0.0314 0.0091 1.0000
15.750 1.2343 0.04611 0.04186 0.0316 0.0090 1.0000
16.000 1.2327 0.04887 0.04474 0.0318 0.0089 1.0000
16.250 1.2295 0.05195 0.04794 0.0318 0.0089 1.0000
16.500 1.2305 0.05471 0.05080 0.0314 0.0087 1.0000
16.750 1.2273 0.05812 0.05432 0.0307 0.0085 1.0000
17.000 1.2195 0.06224 0.05858 0.0297 0.0085 1.0000
17.250 1.2115 0.06665 0.06311 0.0283 0.0085 1.0000
17.500 1.2038 0.07128 0.06787 0.0265 0.0083 1.0000
17.750 1.1918 0.07677 0.07349 0.0241 0.0082 1.0000
18.000 1.1849 0.08168 0.07850 0.0217 0.0081 1.0000
18.250 1.1694 0.08823 0.08518 0.0185 0.0081 1.0000
18.500 1.1423 0.09695 0.09410 0.0141 0.0082 1.0000
18.750 1.1359 0.10239 0.09961 0.0110 0.0080 1.0000
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