Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-I (root) (supermarine371i-il) Reynolds number: 200,000 Max Cl/Cd: 57.89 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371i-il-200000.txt Download as CSV file: xf-supermarine371i-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7882 0.04932 0.04460 -0.0446 0.9941 0.0431
-9.500 -0.7795 0.04324 0.03815 -0.0460 0.9856 0.0413
-9.250 -0.7654 0.03844 0.03282 -0.0469 0.9783 0.0407
-9.000 -0.7433 0.03492 0.02881 -0.0480 0.9727 0.0411
-8.750 -0.7190 0.03185 0.02530 -0.0489 0.9673 0.0414
-8.500 -0.6927 0.02928 0.02231 -0.0495 0.9615 0.0417
-8.250 -0.6614 0.02715 0.01983 -0.0509 0.9576 0.0425
-8.000 -0.6337 0.02594 0.01833 -0.0513 0.9517 0.0436
-7.750 -0.6027 0.02338 0.01564 -0.0525 0.9475 0.0459
-7.500 -0.5709 0.02187 0.01411 -0.0537 0.9435 0.0481
-7.250 -0.5437 0.02076 0.01292 -0.0539 0.9383 0.0505
-7.000 -0.5193 0.01985 0.01193 -0.0535 0.9321 0.0530
-6.750 -0.4963 0.01874 0.01077 -0.0530 0.9274 0.0566
-6.500 -0.4795 0.01797 0.01002 -0.0514 0.9211 0.0616
-6.250 -0.4617 0.01729 0.00931 -0.0499 0.9156 0.0673
-6.000 -0.4404 0.01684 0.00894 -0.0489 0.9116 0.0777
-5.750 -0.4188 0.01667 0.00884 -0.0480 0.9065 0.0981
-5.500 -0.4011 0.01612 0.00834 -0.0465 0.9015 0.1250
-5.250 -0.3827 0.01559 0.00789 -0.0451 0.8976 0.1503
-5.000 -0.3632 0.01528 0.00766 -0.0440 0.8934 0.1742
-4.750 -0.3442 0.01495 0.00746 -0.0429 0.8891 0.2028
-4.500 -0.3266 0.01448 0.00721 -0.0415 0.8854 0.2506
-4.250 -0.3142 0.01368 0.00694 -0.0391 0.8822 0.3609
-4.000 -0.3069 0.01296 0.00690 -0.0358 0.8778 0.5051
-3.750 -0.2927 0.01288 0.00738 -0.0328 0.8736 0.6351
-3.500 -0.2704 0.01309 0.00757 -0.0314 0.8707 0.6809
-3.250 -0.2462 0.01333 0.00777 -0.0304 0.8683 0.7093
-3.000 -0.2204 0.01359 0.00801 -0.0296 0.8664 0.7291
-2.750 -0.1982 0.01393 0.00833 -0.0284 0.8632 0.7459
-2.500 -0.1762 0.01428 0.00867 -0.0271 0.8595 0.7619
-2.250 -0.1524 0.01457 0.00892 -0.0261 0.8568 0.7751
-2.000 -0.1284 0.01477 0.00906 -0.0253 0.8545 0.7865
-1.750 -0.1010 0.01503 0.00932 -0.0247 0.8525 0.7969
-1.500 -0.0743 0.01524 0.00950 -0.0241 0.8507 0.8069
-1.250 -0.0586 0.01562 0.00987 -0.0222 0.8464 0.8177
-1.000 -0.0354 0.01593 0.01020 -0.0211 0.8429 0.8253
-0.750 -0.0123 0.01604 0.01026 -0.0203 0.8397 0.8335
-0.500 0.0170 0.01616 0.01039 -0.0201 0.8375 0.8396
-0.250 0.0432 0.01625 0.01044 -0.0194 0.8353 0.8492
0.000 0.0582 0.01668 0.01092 -0.0173 0.8292 0.8563
0.250 0.0793 0.01677 0.01100 -0.0162 0.8251 0.8638
0.500 0.1090 0.01681 0.01105 -0.0163 0.8226 0.8682
0.750 0.1395 0.01682 0.01105 -0.0165 0.8206 0.8728
1.000 0.1500 0.01715 0.01140 -0.0142 0.8139 0.8798
1.250 0.1768 0.01721 0.01149 -0.0139 0.8096 0.8837
1.500 0.2104 0.01702 0.01132 -0.0144 0.8064 0.8883
1.750 0.2300 0.01706 0.01138 -0.0128 0.7997 0.8955
2.000 0.2589 0.01699 0.01136 -0.0126 0.7939 0.9003
2.250 0.2921 0.01679 0.01118 -0.0131 0.7908 0.9051
2.500 0.3119 0.01683 0.01127 -0.0118 0.7838 0.9112
2.750 0.3468 0.01651 0.01098 -0.0123 0.7774 0.9153
3.000 0.3855 0.01601 0.01050 -0.0133 0.7733 0.9192
3.250 0.4052 0.01598 0.01056 -0.0118 0.7635 0.9267
3.500 0.4462 0.01531 0.00990 -0.0130 0.7554 0.9296
3.750 0.4788 0.01485 0.00950 -0.0134 0.7452 0.9329
4.000 0.5060 0.01455 0.00926 -0.0130 0.7356 0.9376
4.250 0.5390 0.01394 0.00867 -0.0131 0.7261 0.9412
4.500 0.5743 0.01348 0.00827 -0.0141 0.7124 0.9437
4.750 0.6081 0.01306 0.00791 -0.0148 0.6968 0.9470
5.000 0.6364 0.01273 0.00770 -0.0147 0.6775 0.9524
5.250 0.6673 0.01237 0.00739 -0.0149 0.6500 0.9572
5.500 0.7011 0.01211 0.00713 -0.0159 0.5912 0.9611
5.750 0.7212 0.01254 0.00684 -0.0143 0.4623 0.9682
6.000 0.7400 0.01393 0.00751 -0.0139 0.3321 0.9749
6.250 0.7586 0.01532 0.00831 -0.0139 0.2260 0.9837
6.500 0.7844 0.01668 0.00920 -0.0153 0.1528 0.9911
6.750 0.8129 0.01789 0.01015 -0.0171 0.1134 0.9988
7.000 0.8041 0.01815 0.01039 -0.0113 0.1033 1.0000
7.250 0.7922 0.01852 0.01066 -0.0047 0.0961 1.0000
7.500 0.7946 0.01915 0.01121 -0.0007 0.0854 1.0000
7.750 0.8030 0.01982 0.01187 0.0023 0.0757 1.0000
8.000 0.8115 0.02078 0.01278 0.0051 0.0684 1.0000
8.250 0.8240 0.02163 0.01360 0.0071 0.0623 1.0000
8.500 0.8381 0.02278 0.01474 0.0089 0.0573 1.0000
8.750 0.8545 0.02361 0.01560 0.0104 0.0528 1.0000
9.000 0.8778 0.02533 0.01721 0.0106 0.0487 1.0000
9.250 0.8986 0.02625 0.01827 0.0116 0.0466 1.0000
9.500 0.9194 0.02731 0.01943 0.0124 0.0438 1.0000
9.750 0.9385 0.02836 0.02047 0.0132 0.0413 1.0000
10.000 0.9778 0.03118 0.02340 0.0108 0.0391 1.0000
10.250 0.9965 0.03273 0.02520 0.0119 0.0381 1.0000
10.500 1.0118 0.03437 0.02708 0.0134 0.0367 1.0000
10.750 1.0249 0.03593 0.02885 0.0151 0.0354 1.0000
11.000 1.0370 0.03741 0.03044 0.0167 0.0342 1.0000
11.250 1.0471 0.03936 0.03256 0.0184 0.0334 1.0000
11.500 1.0560 0.04168 0.03505 0.0200 0.0328 1.0000
11.750 1.0614 0.04485 0.03843 0.0217 0.0322 1.0000
12.000 1.0584 0.04783 0.04167 0.0244 0.0321 1.0000
12.250 1.0495 0.05131 0.04543 0.0271 0.0320 1.0000
12.500 1.0362 0.05498 0.04935 0.0296 0.0318 1.0000
12.750 1.0208 0.05844 0.05305 0.0318 0.0318 1.0000
13.000 0.9992 0.06243 0.05727 0.0336 0.0317 1.0000
13.250 0.9872 0.06544 0.06048 0.0347 0.0319 1.0000
13.500 0.9653 0.06994 0.06518 0.0351 0.0318 1.0000
13.750 0.9468 0.07343 0.06889 0.0350 0.0322 1.0000
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Polar data table (+)
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