Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 50.72 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cp-080-050-gn-1000000.txt Download as CSV file: xf-cp-080-050-gn-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=8% T=5% R=1.6
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0603 0.10778 0.10578 -0.0956 0.9757 0.0358
-9.250 -0.0505 0.10453 0.10252 -0.0975 0.9748 0.0368
-9.000 -0.0533 0.09919 0.09716 -0.1013 0.9739 0.0374
-8.750 -0.0381 0.09626 0.09424 -0.1025 0.9733 0.0375
-8.500 -0.0239 0.09351 0.09149 -0.1041 0.9726 0.0377
-8.250 -0.0092 0.09088 0.08886 -0.1059 0.9720 0.0379
-8.000 0.0056 0.08805 0.08604 -0.1080 0.9713 0.0382
-7.750 0.0193 0.08526 0.08325 -0.1100 0.9707 0.0387
-7.500 0.0314 0.08239 0.08038 -0.1117 0.9685 0.0392
-7.250 0.0342 0.07848 0.07646 -0.1142 0.9646 0.0408
-7.000 0.0419 0.07372 0.07168 -0.1183 0.9616 0.0410
-6.750 0.0565 0.07103 0.06900 -0.1195 0.9612 0.0411
-6.500 0.0795 0.06800 0.06596 -0.1226 0.9588 0.0413
-6.250 0.1001 0.06516 0.06311 -0.1256 0.9572 0.0415
-6.000 0.1135 0.06276 0.06071 -0.1270 0.9525 0.0418
-5.750 0.1285 0.06031 0.05826 -0.1289 0.9471 0.0423
-5.500 0.1496 0.05721 0.05513 -0.1327 0.9427 0.0431
-5.250 0.1337 0.05275 0.05062 -0.1379 0.9311 0.0446
-5.000 0.1534 0.04978 0.04763 -0.1387 0.9270 0.0448
-4.750 0.1627 0.04796 0.04581 -0.1376 0.9181 0.0449
-4.500 0.1749 0.04597 0.04380 -0.1381 0.9111 0.0450
-4.250 0.1800 0.04442 0.04224 -0.1370 0.9030 0.0452
-4.000 0.1860 0.04271 0.04050 -0.1367 0.8937 0.0454
-3.750 0.1942 0.04106 0.03885 -0.1367 0.8859 0.0458
-3.500 0.2033 0.03913 0.03689 -0.1372 0.8774 0.0462
-3.250 0.2124 0.03716 0.03489 -0.1378 0.8678 0.0469
-3.000 0.2164 0.03120 0.02879 -0.1466 0.8615 0.0486
-2.750 0.2304 0.02939 0.02694 -0.1460 0.8534 0.0488
-2.500 0.2451 0.02787 0.02541 -0.1454 0.8438 0.0489
-2.250 0.2614 0.02640 0.02390 -0.1452 0.8347 0.0490
-2.000 0.2780 0.02500 0.02247 -0.1450 0.8244 0.0493
-1.750 0.2946 0.02364 0.02105 -0.1449 0.8093 0.0496
-1.500 0.3114 0.02226 0.01958 -0.1449 0.7912 0.0501
-1.250 0.3274 0.02093 0.01811 -0.1446 0.7649 0.0511
-1.000 0.3754 0.03047 0.02722 -0.1611 0.7744 0.0529
-0.750 0.3800 0.03005 0.02648 -0.1568 0.7073 0.0531
-0.500 0.3698 0.03055 0.02630 -0.1492 0.5584 0.0532
-0.250 0.3450 0.03230 0.02675 -0.1393 0.2292 0.0532
0.000 0.3501 0.03242 0.02634 -0.1354 0.0587 0.0533
0.250 0.3698 0.03162 0.02549 -0.1344 0.0545 0.0536
0.500 0.3902 0.03078 0.02462 -0.1334 0.0528 0.0540
0.750 0.4111 0.02978 0.02356 -0.1325 0.0512 0.0547
1.000 0.4382 0.02538 0.01878 -0.1328 0.0506 0.0576
1.250 0.4572 0.02486 0.01825 -0.1312 0.0494 0.0578
1.500 0.4762 0.02435 0.01772 -0.1296 0.0490 0.0581
1.750 0.4948 0.02386 0.01720 -0.1278 0.0484 0.0585
2.000 0.5138 0.02332 0.01662 -0.1260 0.0480 0.0591
2.250 0.5337 0.02255 0.01576 -0.1243 0.0475 0.0604
2.500 0.5554 0.02013 0.01301 -0.1225 0.0472 0.0629
2.750 0.5747 0.01985 0.01271 -0.1207 0.0467 0.0632
3.000 0.5944 0.01958 0.01241 -0.1190 0.0463 0.0637
3.250 0.6143 0.01927 0.01205 -0.1172 0.0459 0.0644
3.500 0.6356 0.01817 0.01064 -0.1152 0.0454 0.0682
3.750 0.6549 0.01801 0.01047 -0.1134 0.0451 0.0686
4.000 0.6727 0.01800 0.01044 -0.1112 0.0444 0.0690
4.250 0.6888 0.01812 0.01054 -0.1087 0.0439 0.0697
4.500 0.7082 0.01806 0.01044 -0.1067 0.0437 0.0711
4.750 0.7291 0.01778 0.00994 -0.1048 0.0435 0.0742
5.000 0.7483 0.01775 0.00993 -0.1029 0.0433 0.0748
5.250 0.7675 0.01782 0.00999 -0.1010 0.0431 0.0755
5.500 0.7864 0.01794 0.01010 -0.0989 0.0429 0.0767
5.750 0.8053 0.01807 0.01012 -0.0968 0.0427 0.0810
6.000 0.8237 0.01817 0.01024 -0.0948 0.0425 0.0818
6.250 0.8423 0.01835 0.01042 -0.0928 0.0422 0.0830
6.500 0.8608 0.01859 0.01063 -0.0907 0.0420 0.0845
6.750 0.8798 0.01879 0.01080 -0.0888 0.0418 0.0890
7.000 0.8985 0.01901 0.01103 -0.0868 0.0415 0.0900
7.250 0.9187 0.01844 0.01019 -0.0843 0.0412 0.0676
7.500 0.9377 0.01863 0.01038 -0.0824 0.0409 0.0679
7.750 0.9568 0.01892 0.01069 -0.0805 0.0406 0.0683
8.000 0.9764 0.01929 0.01107 -0.0788 0.0404 0.0685
8.250 0.9961 0.01964 0.01143 -0.0771 0.0401 0.0688
8.500 1.0164 0.02005 0.01184 -0.0755 0.0398 0.0692
8.750 1.0380 0.02053 0.01232 -0.0741 0.0396 0.0696
9.000 1.0644 0.02123 0.01301 -0.0737 0.0392 0.0704
9.250 1.1100 0.02253 0.01428 -0.0767 0.0388 0.0717
9.500 1.1285 0.02285 0.01465 -0.0747 0.0387 0.0721
9.750 1.1475 0.02320 0.01507 -0.0728 0.0385 0.0728
10.000 1.1702 0.02370 0.01561 -0.0717 0.0383 0.0737
10.250 1.1947 0.02428 0.01625 -0.0708 0.0381 0.0754
10.500 1.2181 0.02485 0.01687 -0.0698 0.0379 0.0767
10.750 1.2406 0.02545 0.01753 -0.0686 0.0375 0.0789
11.000 1.2638 0.02611 0.01825 -0.0676 0.0371 0.0831
11.250 1.2872 0.02681 0.01905 -0.0667 0.0369 0.1059
11.500 1.3464 0.02708 0.02083 -0.0736 0.0364 1.0000
11.750 1.3670 0.02786 0.02163 -0.0723 0.0362 1.0000
12.000 1.3864 0.02861 0.02241 -0.0707 0.0359 1.0000
12.250 1.4053 0.02938 0.02321 -0.0691 0.0357 1.0000
12.500 1.4246 0.03025 0.02411 -0.0676 0.0355 1.0000
12.750 1.4425 0.03105 0.02493 -0.0659 0.0354 1.0000
13.000 1.4579 0.03173 0.02562 -0.0639 0.0352 1.0000
13.250 1.4746 0.03260 0.02652 -0.0621 0.0350 1.0000
13.500 1.4926 0.03369 0.02764 -0.0606 0.0348 1.0000
13.750 1.5129 0.03524 0.02924 -0.0596 0.0346 1.0000
14.000 1.5236 0.03856 0.03283 -0.0577 0.0341 1.0000
14.250 1.5241 0.03925 0.03365 -0.0535 0.0339 1.0000
14.500 1.5258 0.04064 0.03521 -0.0498 0.0337 1.0000
14.750 1.5270 0.04246 0.03721 -0.0463 0.0335 1.0000
15.000 1.5242 0.04467 0.03964 -0.0426 0.0333 1.0000
15.250 1.5186 0.04723 0.04242 -0.0388 0.0330 1.0000
15.500 1.5072 0.05025 0.04567 -0.0348 0.0328 1.0000
15.750 1.4946 0.05322 0.04886 -0.0310 0.0326 1.0000
16.000 1.4774 0.05668 0.05254 -0.0274 0.0324 1.0000
16.250 1.4553 0.06065 0.05674 -0.0239 0.0323 1.0000
16.500 1.4184 0.06645 0.06283 -0.0207 0.0323 1.0000
16.750 1.3822 0.07235 0.06900 -0.0186 0.0322 1.0000
17.000 1.3552 0.07749 0.07432 -0.0177 0.0321 1.0000
17.250 1.3080 0.08574 0.08283 -0.0183 0.0321 1.0000
17.500 1.1996 0.10534 0.10291 -0.0267 0.0328 1.0000
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Polar data table (+)
Polar graphs
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