Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Supermarine 371-I (root) (supermarine371i-il) Reynolds number: 100,000 Max Cl/Cd: 40.99 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-supermarine371i-il-100000-n5.txt Download as CSV file: xf-supermarine371i-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6038 0.08904 0.08387 -0.0444 1.0000 0.0331
-12.000 -0.6411 0.07707 0.07181 -0.0528 1.0000 0.0321
-11.750 -0.6759 0.06884 0.06346 -0.0577 1.0000 0.0313
-11.500 -0.7023 0.06338 0.05782 -0.0596 1.0000 0.0314
-11.250 -0.7265 0.05881 0.05306 -0.0599 1.0000 0.0312
-11.000 -0.7455 0.05534 0.04939 -0.0588 1.0000 0.0316
-10.750 -0.7631 0.05221 0.04604 -0.0565 1.0000 0.0316
-10.500 -0.7777 0.04966 0.04328 -0.0533 1.0000 0.0319
-10.250 -0.7878 0.04720 0.04059 -0.0500 1.0000 0.0321
-10.000 -0.7961 0.04492 0.03807 -0.0464 1.0000 0.0324
-9.750 -0.8074 0.04326 0.03621 -0.0416 0.9998 0.0326
-9.500 -0.7911 0.04006 0.03250 -0.0422 0.9854 0.0332
-9.250 -0.7699 0.03730 0.02925 -0.0430 0.9760 0.0340
-9.000 -0.7456 0.03505 0.02652 -0.0438 0.9679 0.0349
-8.750 -0.7184 0.03279 0.02414 -0.0452 0.9618 0.0367
-8.500 -0.6915 0.03119 0.02240 -0.0462 0.9549 0.0385
-8.250 -0.6623 0.02956 0.02055 -0.0472 0.9491 0.0403
-8.000 -0.6329 0.02806 0.01883 -0.0481 0.9437 0.0420
-7.750 -0.6052 0.02681 0.01738 -0.0485 0.9375 0.0438
-7.500 -0.5784 0.02538 0.01591 -0.0491 0.9327 0.0464
-7.250 -0.5567 0.02437 0.01486 -0.0488 0.9261 0.0499
-7.000 -0.5338 0.02347 0.01382 -0.0484 0.9202 0.0539
-6.750 -0.5129 0.02251 0.01283 -0.0477 0.9148 0.0578
-6.500 -0.4945 0.02180 0.01212 -0.0465 0.9080 0.0640
-6.250 -0.4723 0.02122 0.01167 -0.0460 0.9029 0.0734
-6.000 -0.4502 0.02084 0.01127 -0.0453 0.8977 0.0912
-5.750 -0.4291 0.02043 0.01077 -0.0443 0.8925 0.1127
-5.500 -0.4084 0.01982 0.01019 -0.0435 0.8883 0.1321
-5.250 -0.3876 0.01931 0.00976 -0.0427 0.8843 0.1532
-5.000 -0.3689 0.01888 0.00943 -0.0415 0.8793 0.1791
-4.500 -0.3293 0.01783 0.00875 -0.0394 0.8716 0.2694
-4.250 -0.3178 0.01715 0.00853 -0.0370 0.8664 0.3611
-4.000 -0.3063 0.01649 0.00846 -0.0342 0.8621 0.4812
-3.750 -0.2845 0.01653 0.00912 -0.0319 0.8593 0.5976
-3.500 -0.2631 0.01664 0.00912 -0.0305 0.8566 0.6587
-3.250 -0.2426 0.01684 0.00927 -0.0289 0.8526 0.6875
-3.000 -0.2208 0.01706 0.00941 -0.0276 0.8486 0.7090
-2.750 -0.1988 0.01724 0.00950 -0.0263 0.8454 0.7296
-2.500 -0.1738 0.01747 0.00966 -0.0253 0.8430 0.7468
-2.250 -0.1484 0.01766 0.00976 -0.0245 0.8410 0.7618
-2.000 -0.1276 0.01792 0.00999 -0.0231 0.8372 0.7753
-1.750 -0.1038 0.01817 0.01021 -0.0221 0.8335 0.7860
-1.500 -0.0804 0.01829 0.01026 -0.0213 0.8305 0.7949
-1.250 -0.0545 0.01843 0.01035 -0.0208 0.8282 0.8033
-1.000 -0.0277 0.01853 0.01040 -0.0205 0.8261 0.8115
-0.750 -0.0066 0.01872 0.01056 -0.0193 0.8224 0.8204
-0.500 0.0147 0.01892 0.01075 -0.0183 0.8185 0.8272
-0.250 0.0389 0.01904 0.01085 -0.0177 0.8152 0.8339
0.000 0.0638 0.01907 0.01084 -0.0173 0.8123 0.8398
0.250 0.0942 0.01912 0.01088 -0.0177 0.8101 0.8444
0.500 0.1093 0.01935 0.01112 -0.0157 0.8041 0.8530
0.750 0.1361 0.01951 0.01131 -0.0154 0.8000 0.8606
1.000 0.1619 0.01957 0.01139 -0.0148 0.7967 0.8705
1.250 0.1962 0.01963 0.01149 -0.0156 0.7944 0.8777
1.500 0.2103 0.01991 0.01182 -0.0136 0.7875 0.8865
1.750 0.2404 0.01999 0.01195 -0.0140 0.7834 0.8914
2.000 0.2708 0.01992 0.01191 -0.0145 0.7802 0.8955
2.250 0.2891 0.02003 0.01207 -0.0132 0.7727 0.9009
2.500 0.3220 0.01989 0.01200 -0.0140 0.7669 0.9039
2.750 0.3533 0.01975 0.01192 -0.0144 0.7610 0.9076
3.000 0.3756 0.01975 0.01200 -0.0136 0.7530 0.9134
3.250 0.4117 0.01940 0.01172 -0.0146 0.7482 0.9163
3.500 0.4375 0.01936 0.01179 -0.0143 0.7370 0.9207
3.750 0.4669 0.01911 0.01163 -0.0143 0.7273 0.9253
4.000 0.5002 0.01855 0.01116 -0.0145 0.7177 0.9296
4.250 0.5321 0.01808 0.01078 -0.0146 0.7024 0.9334
4.500 0.5605 0.01780 0.01063 -0.0145 0.6849 0.9386
4.750 0.5851 0.01762 0.01061 -0.0138 0.6663 0.9460
5.000 0.6171 0.01733 0.01045 -0.0143 0.6405 0.9509
5.250 0.6414 0.01722 0.01048 -0.0138 0.6003 0.9597
5.500 0.6779 0.01661 0.00958 -0.0141 0.5156 0.9631
5.750 0.7017 0.01712 0.00945 -0.0133 0.4106 0.9703
6.000 0.7213 0.01822 0.01002 -0.0129 0.3169 0.9795
6.250 0.7422 0.01935 0.01073 -0.0131 0.2382 0.9905
6.500 0.7574 0.02029 0.01136 -0.0121 0.1872 1.0000
6.750 0.7554 0.02083 0.01174 -0.0074 0.1614 1.0000
7.000 0.7590 0.02146 0.01222 -0.0037 0.1380 1.0000
7.250 0.7661 0.02220 0.01282 -0.0008 0.1192 1.0000
7.500 0.7744 0.02297 0.01348 0.0020 0.1038 1.0000
7.750 0.7840 0.02375 0.01422 0.0046 0.0915 1.0000
8.000 0.7948 0.02457 0.01502 0.0068 0.0809 1.0000
8.250 0.8051 0.02551 0.01593 0.0090 0.0731 1.0000
8.500 0.8175 0.02640 0.01684 0.0108 0.0657 1.0000
8.750 0.8293 0.02745 0.01789 0.0127 0.0604 1.0000
9.000 0.8427 0.02849 0.01899 0.0143 0.0559 1.0000
9.250 0.8547 0.02970 0.02017 0.0158 0.0524 1.0000
9.500 0.8709 0.03084 0.02144 0.0171 0.0488 1.0000
9.750 0.8862 0.03196 0.02265 0.0183 0.0453 1.0000
10.000 0.9006 0.03323 0.02393 0.0194 0.0429 1.0000
10.250 0.9188 0.03482 0.02554 0.0202 0.0411 1.0000
10.500 0.9381 0.03636 0.02732 0.0211 0.0393 1.0000
10.750 0.9539 0.03791 0.02907 0.0221 0.0373 1.0000
11.000 0.9662 0.03937 0.03068 0.0232 0.0354 1.0000
11.250 0.9776 0.04092 0.03230 0.0244 0.0340 1.0000
11.500 0.9910 0.04303 0.03446 0.0252 0.0329 1.0000
11.750 0.9995 0.04541 0.03714 0.0265 0.0321 1.0000
12.000 1.0028 0.04793 0.03999 0.0281 0.0314 1.0000
12.250 1.0012 0.05063 0.04301 0.0298 0.0306 1.0000
12.500 0.9966 0.05340 0.04607 0.0312 0.0297 1.0000
12.750 0.9907 0.05630 0.04922 0.0324 0.0291 1.0000
13.000 0.9827 0.05938 0.05252 0.0333 0.0284 1.0000
13.250 0.9726 0.06278 0.05613 0.0337 0.0278 1.0000
13.500 0.9593 0.06675 0.06032 0.0337 0.0275 1.0000
13.750 0.9438 0.07115 0.06493 0.0331 0.0273 1.0000
14.000 0.9221 0.07675 0.07078 0.0316 0.0273 1.0000
14.250 0.8947 0.08375 0.07802 0.0286 0.0274 1.0000
14.500 0.8426 0.09672 0.09132 0.0209 0.0284 1.0000
14.750 0.7726 0.11880 0.11359 0.0068 0.0306 1.0000
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