Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=1
| Details | Polar file |
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Airfoil: Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Reynolds number: 500,000 Max Cl/Cd: 51.36 at α=8° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-080-050-gn-500000-n1.txt Download as CSV file: xf-cp-080-050-gn-500000-n1.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 = 0.500 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0602 0.09386 0.09036 -0.1196 0.9104 0.0237
-8.250 -0.0461 0.09106 0.08754 -0.1223 0.9054 0.0240
-7.750 -0.0197 0.08559 0.08202 -0.1273 0.8941 0.0251
-7.500 -0.0056 0.08329 0.07969 -0.1294 0.8879 0.0253
-7.250 0.0059 0.08089 0.07728 -0.1311 0.8812 0.0257
-7.000 0.0179 0.07857 0.07492 -0.1328 0.8747 0.0261
-6.750 0.0281 0.07638 0.07271 -0.1340 0.8679 0.0262
-6.500 0.0376 0.07418 0.07049 -0.1352 0.8601 0.0267
-6.250 0.0450 0.07181 0.06809 -0.1362 0.8530 0.0272
-6.000 0.0515 0.06960 0.06586 -0.1368 0.8449 0.0278
-5.750 0.0597 0.06778 0.06402 -0.1372 0.8377 0.0280
-5.500 0.0655 0.06589 0.06214 -0.1373 0.8309 0.0284
-5.250 0.0692 0.06408 0.06031 -0.1371 0.8222 0.0287
-5.000 0.0708 0.06235 0.05857 -0.1365 0.8148 0.0290
-4.750 0.0764 0.06034 0.05655 -0.1371 0.8069 0.0294
-4.500 0.0836 0.05820 0.05437 -0.1380 0.7997 0.0297
-4.250 0.0912 0.05568 0.05183 -0.1394 0.7932 0.0304
-4.000 0.1020 0.05355 0.04967 -0.1405 0.7852 0.0309
-3.750 0.1149 0.05162 0.04770 -0.1416 0.7773 0.0312
-3.500 0.1279 0.04966 0.04567 -0.1424 0.7647 0.0315
-3.250 0.1376 0.04798 0.04381 -0.1422 0.7306 0.0319
-3.000 0.1495 0.04613 0.04182 -0.1423 0.7054 0.0324
-2.750 0.1550 0.04471 0.04009 -0.1406 0.6464 0.0328
-2.500 0.1303 0.04583 0.04003 -0.1319 0.3617 0.0329
-2.250 0.1290 0.04534 0.03879 -0.1288 0.1043 0.0333
-2.000 0.1456 0.04307 0.03634 -0.1295 0.0456 0.0341
-1.750 0.1656 0.04139 0.03458 -0.1300 0.0397 0.0345
-1.500 0.1864 0.03963 0.03274 -0.1304 0.0386 0.0348
-1.250 0.2075 0.03783 0.03086 -0.1308 0.0379 0.0353
-1.000 0.2291 0.03594 0.02888 -0.1311 0.0372 0.0358
-0.750 0.2509 0.03389 0.02671 -0.1314 0.0363 0.0365
-0.500 0.2731 0.03152 0.02419 -0.1316 0.0359 0.0375
-0.250 0.2951 0.03015 0.02273 -0.1312 0.0355 0.0379
0.000 0.3172 0.02867 0.02114 -0.1307 0.0350 0.0383
0.250 0.3392 0.02705 0.01937 -0.1300 0.0347 0.0389
0.500 0.3612 0.02521 0.01735 -0.1293 0.0344 0.0397
0.750 0.3822 0.02237 0.01418 -0.1283 0.0341 0.0412
1.000 0.4029 0.02110 0.01275 -0.1269 0.0339 0.0417
1.250 0.4235 0.01947 0.01086 -0.1254 0.0337 0.0425
1.500 0.4436 0.01670 0.00754 -0.1239 0.0335 0.0448
1.750 0.4653 0.01634 0.00707 -0.1224 0.0332 0.0451
2.000 0.4869 0.01604 0.00668 -0.1209 0.0331 0.0455
2.250 0.5086 0.01580 0.00634 -0.1194 0.0329 0.0460
2.500 0.5304 0.01562 0.00609 -0.1178 0.0326 0.0464
2.750 0.5521 0.01547 0.00587 -0.1163 0.0323 0.0468
3.000 0.5738 0.01538 0.00572 -0.1147 0.0319 0.0473
3.250 0.5954 0.01531 0.00559 -0.1132 0.0315 0.0479
3.500 0.6169 0.01530 0.00553 -0.1116 0.0311 0.0484
3.750 0.6383 0.01535 0.00556 -0.1100 0.0311 0.0486
4.000 0.6597 0.01546 0.00566 -0.1084 0.0308 0.0487
4.250 0.6810 0.01557 0.00576 -0.1068 0.0307 0.0489
4.500 0.7020 0.01570 0.00588 -0.1051 0.0306 0.0491
4.750 0.7227 0.01584 0.00601 -0.1034 0.0304 0.0492
5.000 0.7433 0.01598 0.00616 -0.1017 0.0304 0.0494
5.250 0.7637 0.01615 0.00632 -0.0999 0.0302 0.0496
5.500 0.7840 0.01632 0.00649 -0.0982 0.0301 0.0498
5.750 0.8040 0.01652 0.00668 -0.0964 0.0300 0.0500
6.000 0.8237 0.01673 0.00691 -0.0945 0.0299 0.0506
6.250 0.8434 0.01694 0.00713 -0.0927 0.0298 0.0508
6.500 0.8630 0.01718 0.00738 -0.0909 0.0297 0.0513
6.750 0.8822 0.01743 0.00764 -0.0890 0.0297 0.0515
7.000 0.9009 0.01771 0.00794 -0.0870 0.0296 0.0516
7.250 0.9197 0.01800 0.00824 -0.0851 0.0295 0.0518
7.500 0.9384 0.01831 0.00857 -0.0832 0.0294 0.0519
7.750 0.9568 0.01863 0.00892 -0.0812 0.0291 0.0522
8.000 0.9748 0.01898 0.00929 -0.0793 0.0290 0.0523
8.250 0.9928 0.01934 0.00967 -0.0773 0.0287 0.0524
8.500 1.0107 0.01972 0.01008 -0.0753 0.0285 0.0526
8.750 1.0281 0.02013 0.01052 -0.0733 0.0283 0.0528
9.000 1.0454 0.02055 0.01097 -0.0714 0.0281 0.0531
9.250 1.0625 0.02100 0.01145 -0.0693 0.0281 0.0533
9.500 1.0797 0.02146 0.01194 -0.0674 0.0279 0.0535
9.750 1.0963 0.02195 0.01246 -0.0654 0.0277 0.0538
10.000 1.1129 0.02246 0.01301 -0.0634 0.0276 0.0544
10.250 1.1295 0.02297 0.01357 -0.0615 0.0274 0.0552
10.500 1.1457 0.02353 0.01416 -0.0595 0.0274 0.0555
10.750 1.1621 0.02408 0.01474 -0.0576 0.0272 0.0565
11.000 1.1781 0.02467 0.01538 -0.0556 0.0271 0.0571
11.250 1.1942 0.02527 0.01602 -0.0538 0.0270 0.0577
11.500 1.2100 0.02589 0.01667 -0.0519 0.0268 0.0581
11.750 1.2257 0.02653 0.01735 -0.0500 0.0267 0.0588
12.000 1.2418 0.02714 0.01800 -0.0482 0.0265 0.0596
12.250 1.2577 0.02777 0.01867 -0.0465 0.0263 0.0608
13.000 1.3021 0.02992 0.02118 -0.0410 0.0259 0.2267
13.750 1.3825 0.03217 0.02472 -0.0438 0.0255 1.0000
14.000 1.3961 0.03311 0.02571 -0.0420 0.0254 1.0000
14.250 1.4097 0.03406 0.02671 -0.0402 0.0253 1.0000
14.500 1.4227 0.03508 0.02778 -0.0385 0.0251 1.0000
14.750 1.4354 0.03613 0.02889 -0.0368 0.0250 1.0000
15.000 1.4480 0.03719 0.03001 -0.0351 0.0248 1.0000
15.250 1.4600 0.03832 0.03121 -0.0334 0.0247 1.0000
15.500 1.4715 0.03950 0.03246 -0.0317 0.0245 1.0000
15.750 1.4829 0.04069 0.03371 -0.0300 0.0244 1.0000
16.000 1.4936 0.04198 0.03508 -0.0284 0.0243 1.0000
16.250 1.5036 0.04331 0.03649 -0.0268 0.0242 1.0000
16.500 1.5132 0.04471 0.03797 -0.0252 0.0240 1.0000
16.750 1.5225 0.04614 0.03948 -0.0237 0.0239 1.0000
17.000 1.5310 0.04764 0.04107 -0.0222 0.0237 1.0000
17.250 1.5388 0.04926 0.04277 -0.0207 0.0236 1.0000
17.500 1.5465 0.05083 0.04442 -0.0194 0.0233 1.0000
17.750 1.5528 0.05263 0.04631 -0.0180 0.0233 1.0000
18.000 1.5590 0.05441 0.04817 -0.0168 0.0231 1.0000
18.250 1.5645 0.05632 0.05018 -0.0157 0.0230 1.0000
18.500 1.5686 0.05841 0.05237 -0.0146 0.0230 1.0000
18.750 1.5727 0.06054 0.05458 -0.0136 0.0229 1.0000
19.000 1.5753 0.06288 0.05702 -0.0128 0.0228 1.0000
19.250 1.5762 0.06549 0.05975 -0.0120 0.0227 1.0000
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Polar data table (+)
Polar graphs
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