Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 48.24 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cp-100-050-gn-1000000.txt Download as CSV file: xf-cp-100-050-gn-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=10% T=5% R=1.3
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0086 0.11347 0.11129 -0.1329 0.9720 0.0283
-10.250 -0.0060 0.11122 0.10904 -0.1329 0.9677 0.0284
-10.000 0.0056 0.10810 0.10592 -0.1345 0.9660 0.0285
-9.750 0.0207 0.10563 0.10344 -0.1364 0.9647 0.0286
-9.500 0.0363 0.10314 0.10095 -0.1388 0.9636 0.0288
-9.250 0.0529 0.10074 0.09855 -0.1413 0.9625 0.0291
-9.000 0.0699 0.09826 0.09606 -0.1441 0.9614 0.0295
-8.750 0.0879 0.09564 0.09344 -0.1473 0.9603 0.0303
-8.500 0.1060 0.09213 0.08990 -0.1521 0.9592 0.0314
-8.250 0.1125 0.08954 0.08730 -0.1543 0.9545 0.0315
-8.000 0.1268 0.08658 0.08434 -0.1565 0.9516 0.0316
-7.750 0.1456 0.08416 0.08191 -0.1586 0.9495 0.0318
-7.500 0.1680 0.08176 0.07950 -0.1621 0.9480 0.0320
-7.250 0.1922 0.07925 0.07697 -0.1664 0.9465 0.0323
-7.000 0.2180 0.07676 0.07446 -0.1711 0.9447 0.0329
-6.750 0.2256 0.07509 0.07280 -0.1709 0.9387 0.0335
-6.500 0.2421 0.07240 0.07008 -0.1745 0.9339 0.0347
-6.250 0.2594 0.06924 0.06686 -0.1817 0.9280 0.0349
-6.000 0.2671 0.06726 0.06489 -0.1801 0.9227 0.0350
-5.750 0.2821 0.06539 0.06302 -0.1805 0.9185 0.0351
-5.500 0.3019 0.06348 0.06108 -0.1828 0.9146 0.0353
-5.250 0.3084 0.06226 0.05987 -0.1817 0.9087 0.0356
-5.000 0.3160 0.06107 0.05867 -0.1810 0.9026 0.0361
-4.750 0.3326 0.05927 0.05682 -0.1830 0.8957 0.0366
-4.500 0.3401 0.05775 0.05532 -0.1828 0.8912 0.0375
-4.250 0.3516 0.05497 0.05246 -0.1893 0.8832 0.0383
-4.000 0.3664 0.05272 0.05019 -0.1893 0.8784 0.0385
-3.750 0.3761 0.05128 0.04877 -0.1878 0.8720 0.0386
-3.500 0.3932 0.04973 0.04717 -0.1883 0.8645 0.0387
-3.250 0.4075 0.04837 0.04580 -0.1883 0.8588 0.0389
-3.000 0.4231 0.04699 0.04441 -0.1887 0.8529 0.0393
-2.750 0.4439 0.04538 0.04275 -0.1903 0.8460 0.0398
-2.500 0.4596 0.04388 0.04125 -0.1907 0.8396 0.0405
-2.250 0.4981 0.04029 0.03750 -0.1999 0.8327 0.0420
-2.000 0.5138 0.03842 0.03560 -0.1994 0.8268 0.0421
-1.750 0.5297 0.03711 0.03430 -0.1985 0.8195 0.0422
-1.500 0.5495 0.03585 0.03298 -0.1985 0.8115 0.0424
-1.250 0.5686 0.03467 0.03179 -0.1983 0.8034 0.0427
-1.000 0.5893 0.03348 0.03053 -0.1984 0.7932 0.0431
-0.750 0.6092 0.03226 0.02926 -0.1983 0.7805 0.0436
-0.500 0.6315 0.03089 0.02781 -0.1986 0.7677 0.0448
0.000 0.6800 0.02659 0.02316 -0.2003 0.7276 0.0461
0.250 0.6778 0.02631 0.02263 -0.1944 0.6765 0.0463
0.500 0.6603 0.02640 0.02238 -0.1850 0.6073 0.0463
0.750 0.6393 0.02698 0.02245 -0.1752 0.4991 0.0464
1.000 0.6078 0.02851 0.02310 -0.1638 0.2988 0.0464
1.250 0.5894 0.02978 0.02357 -0.1554 0.0519 0.0464
1.500 0.6100 0.02907 0.02280 -0.1547 0.0438 0.0467
1.750 0.6325 0.02830 0.02199 -0.1542 0.0416 0.0472
2.000 0.6563 0.02747 0.02109 -0.1540 0.0401 0.0481
2.250 0.6961 0.02457 0.01791 -0.1565 0.0389 0.0505
2.500 0.7168 0.02417 0.01749 -0.1555 0.0384 0.0507
2.750 0.7383 0.02377 0.01705 -0.1546 0.0376 0.0510
3.000 0.7603 0.02337 0.01661 -0.1537 0.0370 0.0515
3.250 0.7830 0.02290 0.01608 -0.1528 0.0367 0.0525
3.500 0.8140 0.02100 0.01387 -0.1529 0.0364 0.0555
3.750 0.8334 0.02096 0.01381 -0.1514 0.0359 0.0559
4.000 0.8535 0.02080 0.01362 -0.1500 0.0356 0.0564
4.250 0.8737 0.02062 0.01337 -0.1485 0.0353 0.0575
4.500 0.8970 0.01966 0.01211 -0.1470 0.0351 0.0607
4.750 0.9145 0.01974 0.01219 -0.1451 0.0349 0.0612
5.000 0.9317 0.01987 0.01230 -0.1431 0.0345 0.0617
5.250 0.9487 0.02003 0.01244 -0.1410 0.0344 0.0628
5.500 0.9654 0.02005 0.01227 -0.1386 0.0341 0.0667
5.750 0.9775 0.02047 0.01272 -0.1358 0.0338 0.0673
6.000 0.9898 0.02098 0.01323 -0.1330 0.0336 0.0679
6.250 1.0070 0.02123 0.01348 -0.1310 0.0335 0.0695
6.500 1.0263 0.02133 0.01345 -0.1292 0.0332 0.0734
6.750 1.0424 0.02161 0.01375 -0.1272 0.0329 0.0743
7.000 1.0578 0.02203 0.01419 -0.1249 0.0328 0.0755
7.250 1.0733 0.02250 0.01464 -0.1227 0.0326 0.0774
7.500 1.0887 0.02293 0.01505 -0.1206 0.0323 0.0820
7.750 1.1039 0.02345 0.01559 -0.1184 0.0321 0.0841
8.000 1.1197 0.02402 0.01615 -0.1163 0.0319 0.0864
8.250 1.1372 0.02386 0.01576 -0.1137 0.0318 0.0603
8.500 1.1529 0.02444 0.01636 -0.1117 0.0316 0.0606
8.750 1.1693 0.02504 0.01699 -0.1098 0.0314 0.0609
9.000 1.1866 0.02567 0.01765 -0.1080 0.0313 0.0617
9.250 1.2045 0.02625 0.01825 -0.1064 0.0310 0.0622
9.500 1.2235 0.02687 0.01889 -0.1049 0.0309 0.0627
9.750 1.2429 0.02746 0.01950 -0.1035 0.0306 0.0630
10.000 1.2631 0.02807 0.02011 -0.1022 0.0304 0.0642
10.250 1.2812 0.02865 0.02070 -0.1007 0.0300 0.0648
10.500 1.3025 0.02929 0.02134 -0.0997 0.0298 0.0657
10.750 1.3279 0.02996 0.02200 -0.0992 0.0294 0.0677
11.000 1.4070 0.03130 0.02331 -0.1066 0.0289 0.0741
11.250 1.4144 0.03182 0.02399 -0.1033 0.0288 0.1164
11.500 1.4561 0.03206 0.02553 -0.1071 0.0285 1.0000
11.750 1.4767 0.03290 0.02642 -0.1058 0.0284 1.0000
12.000 1.4998 0.03387 0.02746 -0.1050 0.0282 1.0000
12.250 1.5250 0.03502 0.02868 -0.1045 0.0281 1.0000
12.500 1.5503 0.03635 0.03010 -0.1040 0.0280 1.0000
12.750 1.5690 0.03760 0.03146 -0.1026 0.0276 1.0000
13.000 1.5865 0.03892 0.03288 -0.1011 0.0273 1.0000
13.250 1.6055 0.04063 0.03472 -0.0998 0.0271 1.0000
13.500 1.6215 0.04257 0.03682 -0.0982 0.0270 1.0000
13.750 1.6347 0.04475 0.03917 -0.0963 0.0268 1.0000
14.000 1.6447 0.04830 0.04300 -0.0940 0.0270 1.0000
14.250 1.6447 0.05257 0.04758 -0.0908 0.0277 1.0000
14.500 1.6422 0.05592 0.05111 -0.0874 0.0281 1.0000
14.750 1.6036 0.05442 0.04973 -0.0814 0.0293 1.0000
15.750 1.5598 0.07352 0.06978 -0.0671 0.0277 1.0000
16.000 1.5389 0.07756 0.07403 -0.0641 0.0272 1.0000
16.250 1.5158 0.08211 0.07876 -0.0617 0.0271 1.0000
16.500 1.4944 0.08651 0.08332 -0.0600 0.0269 1.0000
16.750 1.4710 0.09140 0.08838 -0.0589 0.0267 1.0000
17.000 1.4458 0.09690 0.09405 -0.0585 0.0266 1.0000
17.250 1.4189 0.10305 0.10036 -0.0590 0.0265 1.0000
17.500 1.3902 0.10990 0.10737 -0.0605 0.0264 1.0000
17.750 1.3582 0.11791 0.11554 -0.0634 0.0263 1.0000
18.000 1.3143 0.12920 0.12703 -0.0691 0.0264 1.0000
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