Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| 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: 57.94 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cp-080-050-gn-1000000-n5.txt Download as CSV file: xf-cp-080-050-gn-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1275 0.09958 0.09734 -0.1022 0.9694 0.0285
-8.500 -0.1190 0.09743 0.09520 -0.1029 0.9654 0.0288
-8.000 -0.1067 0.08873 0.08645 -0.1092 0.9600 0.0308
-7.750 -0.0882 0.08662 0.08434 -0.1119 0.9583 0.0309
-7.500 -0.0696 0.08417 0.08189 -0.1150 0.9567 0.0311
-7.250 -0.0553 0.08230 0.08003 -0.1165 0.9526 0.0313
-7.000 -0.0361 0.08012 0.07783 -0.1194 0.9473 0.0315
-6.750 -0.0206 0.07744 0.07515 -0.1224 0.9458 0.0317
-6.250 0.0115 0.06858 0.06622 -0.1343 0.9379 0.0340
-6.000 0.0398 0.06654 0.06414 -0.1388 0.9281 0.0342
-5.750 0.0584 0.06452 0.06211 -0.1416 0.9229 0.0344
-5.500 0.0724 0.06261 0.06018 -0.1434 0.9143 0.0346
-4.500 0.1001 0.05116 0.04856 -0.1522 0.8785 0.0374
-4.250 0.1159 0.04958 0.04694 -0.1532 0.8717 0.0376
-4.000 0.1313 0.04825 0.04558 -0.1536 0.8616 0.0377
-3.750 0.1472 0.04662 0.04390 -0.1544 0.8529 0.0379
-3.500 0.1636 0.04530 0.04253 -0.1547 0.8410 0.0381
-3.250 0.1799 0.04367 0.04085 -0.1553 0.8297 0.0385
-2.750 0.2082 0.03569 0.03261 -0.1602 0.8117 0.0411
-2.500 0.2273 0.03453 0.03136 -0.1599 0.7971 0.0412
-1.500 0.2844 0.01350 0.00877 -0.1619 0.7633 0.0487
-1.250 0.3053 0.01325 0.00839 -0.1602 0.7412 0.0488
-1.000 0.3257 0.01322 0.00825 -0.1584 0.7137 0.0490
-0.750 0.3410 0.01330 0.00809 -0.1555 0.6684 0.0491
-0.500 0.3520 0.01353 0.00799 -0.1517 0.5977 0.0492
-0.250 0.3367 0.01511 0.00845 -0.1430 0.3339 0.0492
0.250 0.3581 0.01604 0.00842 -0.1359 0.0496 0.0496
0.500 0.3810 0.01573 0.00803 -0.1347 0.0468 0.0499
0.750 0.4035 0.01540 0.00759 -0.1334 0.0442 0.0502
1.000 0.4258 0.01499 0.00708 -0.1321 0.0431 0.0507
1.250 0.4475 0.01457 0.00653 -0.1306 0.0421 0.0512
1.500 0.4688 0.01422 0.00606 -0.1289 0.0413 0.0518
1.750 0.4902 0.01399 0.00574 -0.1273 0.0406 0.0522
2.000 0.5120 0.01390 0.00557 -0.1257 0.0402 0.0525
2.250 0.5334 0.01381 0.00542 -0.1241 0.0395 0.0528
2.500 0.5545 0.01369 0.00528 -0.1224 0.0390 0.0531
2.750 0.5758 0.01368 0.00525 -0.1207 0.0387 0.0534
3.000 0.5974 0.01369 0.00525 -0.1191 0.0385 0.0536
3.250 0.6190 0.01371 0.00525 -0.1175 0.0383 0.0538
3.500 0.6406 0.01376 0.00530 -0.1158 0.0380 0.0541
3.750 0.6621 0.01382 0.00534 -0.1142 0.0379 0.0544
4.000 0.6834 0.01388 0.00539 -0.1125 0.0375 0.0547
4.250 0.7045 0.01397 0.00547 -0.1108 0.0373 0.0550
4.500 0.7255 0.01407 0.00556 -0.1091 0.0371 0.0554
4.750 0.7464 0.01418 0.00566 -0.1074 0.0368 0.0556
5.000 0.7671 0.01431 0.00579 -0.1056 0.0366 0.0560
5.250 0.7876 0.01445 0.00592 -0.1038 0.0362 0.0564
5.500 0.8078 0.01461 0.00608 -0.1020 0.0359 0.0567
5.750 0.8279 0.01477 0.00623 -0.1001 0.0357 0.0569
6.000 0.8477 0.01497 0.00642 -0.0983 0.0355 0.0571
6.250 0.8672 0.01516 0.00661 -0.0963 0.0352 0.0572
6.500 0.8855 0.01537 0.00683 -0.0942 0.0349 0.0576
6.750 0.9038 0.01560 0.00708 -0.0921 0.0348 0.0578
7.000 0.9214 0.01591 0.00740 -0.0899 0.0346 0.0581
7.250 0.9374 0.01632 0.00783 -0.0874 0.0343 0.0584
7.500 0.9548 0.01665 0.00818 -0.0852 0.0342 0.0586
7.750 0.9733 0.01694 0.00849 -0.0833 0.0341 0.0591
8.000 0.9913 0.01728 0.00885 -0.0812 0.0340 0.0594
8.250 1.0093 0.01761 0.00921 -0.0792 0.0339 0.0598
8.500 1.0269 0.01796 0.00959 -0.0771 0.0338 0.0604
8.750 1.0445 0.01834 0.00998 -0.0750 0.0336 0.0608
9.000 1.0625 0.01871 0.01037 -0.0731 0.0335 0.0612
9.250 1.0804 0.01908 0.01077 -0.0711 0.0333 0.0617
9.500 1.0976 0.01950 0.01121 -0.0691 0.0331 0.0619
9.750 1.1148 0.01993 0.01167 -0.0671 0.0329 0.0625
10.000 1.1321 0.02038 0.01215 -0.0651 0.0327 0.0633
10.250 1.1490 0.02085 0.01266 -0.0631 0.0325 0.0643
10.500 1.1653 0.02139 0.01323 -0.0611 0.0325 0.0649
10.750 1.1827 0.02186 0.01372 -0.0592 0.0322 0.0660
11.000 1.1997 0.02238 0.01427 -0.0573 0.0321 0.0674
11.250 1.2164 0.02291 0.01484 -0.0554 0.0319 0.0698
11.500 1.2328 0.02347 0.01543 -0.0535 0.0317 0.0727
11.750 1.2492 0.02407 0.01607 -0.0516 0.0317 0.0789
12.000 1.2626 0.02415 0.01689 -0.0493 0.0315 0.5921
12.250 1.3338 0.02466 0.01818 -0.0591 0.0312 1.0000
12.500 1.3502 0.02532 0.01885 -0.0573 0.0311 1.0000
12.750 1.3662 0.02599 0.01953 -0.0555 0.0309 1.0000
13.000 1.3818 0.02669 0.02025 -0.0537 0.0308 1.0000
13.250 1.3971 0.02744 0.02101 -0.0519 0.0307 1.0000
13.500 1.4122 0.02822 0.02180 -0.0501 0.0306 1.0000
13.750 1.4267 0.02908 0.02268 -0.0482 0.0304 1.0000
14.000 1.4405 0.03003 0.02365 -0.0463 0.0302 1.0000
14.250 1.4543 0.03102 0.02468 -0.0444 0.0300 1.0000
14.500 1.4685 0.03182 0.02553 -0.0426 0.0299 1.0000
14.750 1.4821 0.03270 0.02646 -0.0408 0.0298 1.0000
15.000 1.4952 0.03358 0.02739 -0.0390 0.0297 1.0000
15.250 1.5081 0.03455 0.02841 -0.0372 0.0296 1.0000
15.500 1.5204 0.03553 0.02945 -0.0354 0.0295 1.0000
15.750 1.5320 0.03658 0.03055 -0.0336 0.0294 1.0000
16.000 1.5433 0.03770 0.03173 -0.0318 0.0293 1.0000
16.250 1.5543 0.03885 0.03294 -0.0301 0.0292 1.0000
16.500 1.5640 0.04010 0.03427 -0.0283 0.0290 1.0000
16.750 1.5736 0.04137 0.03561 -0.0265 0.0289 1.0000
17.000 1.5824 0.04272 0.03704 -0.0248 0.0288 1.0000
17.250 1.5903 0.04418 0.03857 -0.0230 0.0286 1.0000
17.500 1.5981 0.04562 0.04009 -0.0214 0.0285 1.0000
17.750 1.6043 0.04729 0.04184 -0.0197 0.0284 1.0000
18.000 1.6107 0.04890 0.04353 -0.0182 0.0282 1.0000
18.250 1.6156 0.05069 0.04541 -0.0167 0.0281 1.0000
18.500 1.6203 0.05256 0.04736 -0.0153 0.0280 1.0000
18.750 1.6242 0.05451 0.04939 -0.0140 0.0279 1.0000
19.000 1.6282 0.05649 0.05145 -0.0128 0.0277 1.0000
19.250 1.6314 0.05857 0.05360 -0.0118 0.0276 1.0000
19.500 1.6345 0.06073 0.05583 -0.0108 0.0275 1.0000
19.750 1.6355 0.06318 0.05838 -0.0100 0.0274 1.0000
20.000 1.6368 0.06566 0.06094 -0.0093 0.0273 1.0000
20.250 1.6366 0.06837 0.06374 -0.0087 0.0273 1.0000
20.500 1.6366 0.07114 0.06659 -0.0084 0.0272 1.0000
20.750 1.6360 0.07402 0.06955 -0.0082 0.0271 1.0000
21.000 1.6333 0.07724 0.07286 -0.0081 0.0270 1.0000
21.250 1.6315 0.08045 0.07615 -0.0083 0.0270 1.0000
21.500 1.6264 0.08419 0.08000 -0.0087 0.0269 1.0000
21.750 1.6222 0.08790 0.08380 -0.0094 0.0269 1.0000
22.000 1.6169 0.09187 0.08786 -0.0103 0.0268 1.0000
22.250 1.6106 0.09606 0.09215 -0.0115 0.0267 1.0000
22.500 1.6026 0.10063 0.09683 -0.0130 0.0267 1.0000
22.750 1.5925 0.10568 0.10199 -0.0150 0.0266 1.0000
23.000 1.5830 0.11078 0.10719 -0.0173 0.0266 1.0000
23.250 1.5703 0.11658 0.11311 -0.0202 0.0265 1.0000
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Polar data table (+)
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