Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 200,000 Max Cl/Cd: 51.24 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-200000.txt Download as CSV file: xf-supermarine371ii-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4594 0.10241 0.09922 -0.0200 1.0000 0.0275
-9.750 -0.4599 0.09789 0.09473 -0.0224 1.0000 0.0275
-9.500 -0.4617 0.09316 0.09002 -0.0250 1.0000 0.0275
-9.250 -0.4571 0.08723 0.08412 -0.0211 1.0000 0.0309
-9.000 -0.4573 0.08301 0.07991 -0.0225 1.0000 0.0321
-8.750 -0.4594 0.07859 0.07552 -0.0244 1.0000 0.0334
-8.500 -0.4643 0.07377 0.07074 -0.0270 1.0000 0.0345
-8.250 -0.4721 0.06866 0.06566 -0.0304 1.0000 0.0345
-8.000 -0.4845 0.06358 0.06060 -0.0341 1.0000 0.0337
-7.750 -0.4974 0.05941 0.05642 -0.0357 1.0000 0.0337
-7.500 -0.5043 0.05514 0.05210 -0.0368 1.0000 0.0353
-7.250 -0.5082 0.05097 0.04787 -0.0373 1.0000 0.0361
-7.000 -0.5224 0.04877 0.04565 -0.0339 1.0000 0.0367
-6.750 -0.5207 0.04672 0.04319 -0.0338 0.9948 0.0394
-6.500 -0.5731 0.05493 0.05127 -0.0278 0.9996 0.0371
-6.250 -0.5424 0.05184 0.04739 -0.0310 0.9914 0.0403
-6.000 -0.5249 0.04487 0.04052 -0.0337 0.9866 0.0427
-5.750 -0.4970 0.04134 0.03680 -0.0362 0.9826 0.0468
-5.500 -0.4698 0.03841 0.03312 -0.0371 0.9759 0.0542
-5.250 -0.4423 0.03457 0.02932 -0.0393 0.9722 0.0585
-4.500 -0.3470 0.02426 0.01742 -0.0401 0.9597 0.0431
-4.250 -0.3115 0.02088 0.01360 -0.0402 0.9571 0.0334
-4.000 -0.2778 0.01929 0.01171 -0.0411 0.9543 0.0369
-3.750 -0.2496 0.01749 0.00970 -0.0407 0.9495 0.0363
-3.500 -0.2193 0.01611 0.00816 -0.0409 0.9459 0.0379
-3.250 -0.1907 0.01484 0.00687 -0.0412 0.9428 0.0437
-3.000 -0.1676 0.01413 0.00614 -0.0404 0.9374 0.0488
-2.750 -0.1434 0.01339 0.00533 -0.0399 0.9326 0.0583
-2.500 -0.1362 0.01080 0.00453 -0.0372 0.9277 0.4810
-2.250 -0.1351 0.01055 0.00543 -0.0299 0.9215 0.8096
-2.000 -0.1160 0.01091 0.00580 -0.0265 0.9182 0.8558
-1.750 -0.0975 0.01157 0.00645 -0.0216 0.9159 0.9034
-1.500 -0.0502 0.01213 0.00689 -0.0235 0.9161 0.9297
-1.250 -0.0048 0.01218 0.00682 -0.0271 0.9152 0.9348
-1.000 0.0150 0.01221 0.00678 -0.0262 0.9104 0.9416
-0.750 0.0528 0.01220 0.00668 -0.0288 0.9083 0.9438
-0.500 0.0899 0.01218 0.00661 -0.0312 0.9061 0.9463
-0.250 0.1242 0.01217 0.00656 -0.0330 0.9038 0.9497
0.000 0.1506 0.01220 0.00657 -0.0333 0.9013 0.9551
0.250 0.1881 0.01225 0.00663 -0.0360 0.8987 0.9575
0.500 0.2238 0.01229 0.00671 -0.0383 0.8961 0.9608
0.750 0.2557 0.01235 0.00680 -0.0398 0.8934 0.9652
1.000 0.2878 0.01240 0.00690 -0.0413 0.8910 0.9694
1.250 0.3262 0.01242 0.00700 -0.0440 0.8894 0.9723
1.500 0.3613 0.01252 0.00723 -0.0462 0.8870 0.9765
1.750 0.3917 0.01267 0.00751 -0.0476 0.8830 0.9820
2.000 0.4259 0.01233 0.00726 -0.0482 0.8724 0.9850
2.250 0.4454 0.01112 0.00601 -0.0432 0.8363 0.9902
2.500 0.4693 0.01026 0.00510 -0.0404 0.7970 0.9960
2.750 0.4914 0.00959 0.00441 -0.0378 0.7368 1.0000
3.000 0.4786 0.01156 0.00408 -0.0299 0.2130 1.0000
3.250 0.4839 0.01335 0.00507 -0.0265 0.0582 1.0000
3.500 0.4965 0.01400 0.00574 -0.0241 0.0458 1.0000
3.750 0.5066 0.01485 0.00665 -0.0210 0.0417 1.0000
4.000 0.5184 0.01572 0.00756 -0.0180 0.0384 1.0000
4.250 0.5330 0.01673 0.00853 -0.0157 0.0339 1.0000
4.500 0.5517 0.01856 0.01039 -0.0138 0.0305 1.0000
4.750 0.5753 0.02025 0.01222 -0.0125 0.0298 1.0000
5.000 0.6002 0.02272 0.01495 -0.0115 0.0305 1.0000
5.250 0.6291 0.02509 0.01780 -0.0096 0.0381 1.0000
6.250 0.7118 0.03845 0.03283 -0.0015 0.0519 1.0000
6.500 0.7276 0.04105 0.03562 -0.0003 0.0474 1.0000
6.750 0.7425 0.04537 0.03986 0.0000 0.0451 1.0000
7.000 0.7473 0.04829 0.04344 0.0030 0.0413 1.0000
7.250 0.7576 0.05125 0.04673 0.0048 0.0376 1.0000
7.500 0.7654 0.05448 0.05015 0.0061 0.0357 1.0000
7.750 0.7718 0.05781 0.05357 0.0071 0.0340 1.0000
8.000 0.7776 0.06164 0.05744 0.0078 0.0330 1.0000
10.250 0.6944 0.10230 0.09887 0.0029 0.0312 1.0000
10.500 0.6917 0.10820 0.10475 -0.0017 0.0311 1.0000
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Polar data table (+)
Polar graphs
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