Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=1
| 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: 62.15 at α=6° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-100-050-gn-1000000-n1.txt Download as CSV file: xf-cp-100-050-gn-1000000-n1.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 = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0783 0.09338 0.09030 -0.1608 0.8469 0.0169
-9.500 0.0890 0.09140 0.08831 -0.1619 0.8427 0.0170
-9.250 0.0969 0.08886 0.08575 -0.1631 0.8370 0.0174
-9.000 0.1077 0.08708 0.08394 -0.1639 0.8310 0.0175
-8.750 0.1175 0.08508 0.08192 -0.1648 0.8265 0.0177
-8.500 0.1275 0.08312 0.07995 -0.1657 0.8215 0.0179
-8.250 0.1370 0.08121 0.07802 -0.1664 0.8154 0.0183
-8.000 0.1457 0.07924 0.07602 -0.1670 0.8098 0.0185
-7.750 0.1536 0.07708 0.07384 -0.1677 0.8044 0.0193
-7.500 0.1610 0.07500 0.07174 -0.1683 0.7982 0.0197
-7.250 0.1712 0.07351 0.07024 -0.1685 0.7930 0.0197
-7.000 0.1786 0.07146 0.06818 -0.1690 0.7881 0.0199
-6.750 0.1879 0.06989 0.06661 -0.1692 0.7825 0.0203
-6.500 0.1953 0.06825 0.06495 -0.1691 0.7768 0.0205
-6.250 0.2018 0.06655 0.06324 -0.1690 0.7718 0.0208
-6.000 0.2070 0.06494 0.06163 -0.1686 0.7658 0.0211
-5.750 0.2084 0.06342 0.06010 -0.1674 0.7588 0.0217
-5.500 0.2124 0.06143 0.05810 -0.1676 0.7539 0.0223
-5.250 0.2214 0.05962 0.05629 -0.1682 0.7486 0.0225
-5.000 0.2313 0.05795 0.05460 -0.1687 0.7423 0.0227
-4.750 0.2434 0.05635 0.05299 -0.1695 0.7377 0.0228
-4.500 0.2566 0.05471 0.05134 -0.1704 0.7325 0.0232
-4.250 0.2699 0.05287 0.04949 -0.1715 0.7273 0.0236
-4.000 0.2838 0.05107 0.04766 -0.1726 0.7218 0.0242
-3.750 0.2995 0.04889 0.04546 -0.1744 0.7173 0.0248
-3.500 0.3164 0.04692 0.04346 -0.1760 0.7113 0.0251
-3.250 0.3309 0.04508 0.04154 -0.1769 0.6967 0.0254
-3.000 0.3436 0.04380 0.04016 -0.1765 0.6735 0.0256
-2.750 0.3542 0.04266 0.03886 -0.1755 0.6427 0.0259
-2.500 0.3682 0.04134 0.03742 -0.1752 0.6187 0.0262
-2.250 0.3393 0.04231 0.03768 -0.1647 0.4548 0.0263
-2.000 0.3235 0.04250 0.03736 -0.1574 0.3189 0.0265
-1.750 0.3084 0.04277 0.03701 -0.1503 0.0836 0.0267
-1.500 0.3278 0.04100 0.03511 -0.1511 0.0288 0.0275
-1.250 0.3523 0.03887 0.03290 -0.1530 0.0273 0.0280
-1.000 0.3778 0.03685 0.03081 -0.1547 0.0266 0.0284
-0.750 0.4015 0.03553 0.02943 -0.1555 0.0252 0.0286
-0.500 0.4266 0.03406 0.02790 -0.1565 0.0250 0.0290
-0.250 0.4522 0.03259 0.02636 -0.1574 0.0246 0.0296
0.500 0.5358 0.02719 0.02064 -0.1614 0.0238 0.0316
0.750 0.5612 0.02608 0.01945 -0.1616 0.0237 0.0319
1.000 0.5874 0.02484 0.01811 -0.1619 0.0232 0.0325
1.250 0.6159 0.02306 0.01616 -0.1627 0.0229 0.0337
1.500 0.6573 0.01426 0.00595 -0.1671 0.0230 0.0386
1.750 0.6795 0.01426 0.00589 -0.1658 0.0228 0.0388
2.000 0.7015 0.01424 0.00581 -0.1645 0.0226 0.0390
2.250 0.7231 0.01425 0.00577 -0.1631 0.0224 0.0393
2.500 0.7445 0.01427 0.00574 -0.1616 0.0222 0.0396
2.750 0.7657 0.01431 0.00574 -0.1601 0.0219 0.0400
3.000 0.7870 0.01438 0.00577 -0.1586 0.0218 0.0405
3.250 0.8082 0.01445 0.00580 -0.1571 0.0217 0.0408
3.500 0.8292 0.01455 0.00589 -0.1556 0.0217 0.0410
3.750 0.8496 0.01468 0.00599 -0.1539 0.0214 0.0412
4.000 0.8699 0.01482 0.00611 -0.1523 0.0214 0.0414
4.250 0.8902 0.01499 0.00626 -0.1506 0.0213 0.0415
4.500 0.9106 0.01516 0.00642 -0.1490 0.0212 0.0415
4.750 0.9307 0.01535 0.00661 -0.1474 0.0211 0.0416
5.000 0.9502 0.01556 0.00681 -0.1456 0.0210 0.0418
5.250 0.9696 0.01579 0.00704 -0.1438 0.0210 0.0419
5.500 0.9890 0.01603 0.00728 -0.1421 0.0209 0.0419
5.750 1.0086 0.01628 0.00753 -0.1404 0.0207 0.0422
6.000 1.0279 0.01654 0.00780 -0.1386 0.0207 0.0423
6.250 1.0465 0.01684 0.00812 -0.1368 0.0207 0.0426
6.500 1.0649 0.01715 0.00843 -0.1349 0.0206 0.0428
6.750 1.0835 0.01746 0.00875 -0.1331 0.0205 0.0429
7.000 1.1020 0.01779 0.00910 -0.1313 0.0205 0.0431
7.250 1.1199 0.01815 0.00947 -0.1294 0.0205 0.0433
7.500 1.1376 0.01852 0.00986 -0.1275 0.0204 0.0434
7.750 1.1552 0.01891 0.01026 -0.1256 0.0203 0.0435
8.000 1.1727 0.01932 0.01069 -0.1237 0.0203 0.0439
8.250 1.1900 0.01975 0.01113 -0.1218 0.0202 0.0441
8.500 1.2065 0.02021 0.01162 -0.1198 0.0202 0.0444
8.750 1.2233 0.02068 0.01211 -0.1179 0.0201 0.0444
9.000 1.2399 0.02117 0.01263 -0.1160 0.0200 0.0448
9.250 1.2561 0.02169 0.01317 -0.1140 0.0200 0.0449
9.500 1.2719 0.02224 0.01375 -0.1121 0.0199 0.0450
9.750 1.2880 0.02279 0.01432 -0.1102 0.0197 0.0451
10.000 1.3039 0.02336 0.01492 -0.1083 0.0196 0.0454
10.250 1.3195 0.02396 0.01555 -0.1063 0.0194 0.0455
10.500 1.3342 0.02462 0.01624 -0.1043 0.0194 0.0458
10.750 1.3496 0.02525 0.01691 -0.1025 0.0191 0.0464
11.000 1.3642 0.02595 0.01765 -0.1005 0.0191 0.0472
11.250 1.3785 0.02668 0.01841 -0.0986 0.0189 0.0478
11.500 1.3931 0.02741 0.01917 -0.0967 0.0187 0.0482
11.750 1.4075 0.02816 0.01996 -0.0948 0.0187 0.0484
12.000 1.4211 0.02897 0.02081 -0.0929 0.0186 0.0488
12.250 1.4349 0.02980 0.02167 -0.0911 0.0184 0.0496
12.750 1.4620 0.03152 0.02348 -0.0875 0.0182 0.0527
13.000 1.4752 0.03242 0.02445 -0.0857 0.0181 0.0738
13.250 1.4855 0.03281 0.02568 -0.0834 0.0181 0.7711
13.750 1.5581 0.03529 0.02861 -0.0901 0.0178 1.0000
14.000 1.5701 0.03635 0.02969 -0.0883 0.0177 1.0000
14.250 1.5820 0.03743 0.03080 -0.0865 0.0176 1.0000
14.500 1.5936 0.03854 0.03195 -0.0848 0.0176 1.0000
14.750 1.6040 0.03977 0.03322 -0.0829 0.0175 1.0000
15.000 1.6149 0.04095 0.03443 -0.0812 0.0175 1.0000
15.250 1.6244 0.04227 0.03580 -0.0794 0.0173 1.0000
15.500 1.6340 0.04360 0.03718 -0.0776 0.0173 1.0000
15.750 1.6442 0.04489 0.03851 -0.0759 0.0173 1.0000
16.000 1.6533 0.04630 0.03997 -0.0742 0.0171 1.0000
16.250 1.6620 0.04775 0.04147 -0.0726 0.0170 1.0000
16.500 1.6716 0.04913 0.04289 -0.0710 0.0169 1.0000
16.750 1.6793 0.05070 0.04452 -0.0694 0.0168 1.0000
17.000 1.6876 0.05224 0.04612 -0.0679 0.0168 1.0000
17.250 1.6956 0.05383 0.04776 -0.0664 0.0167 1.0000
17.500 1.7030 0.05550 0.04949 -0.0649 0.0166 1.0000
17.750 1.7108 0.05715 0.05119 -0.0635 0.0165 1.0000
18.000 1.7177 0.05891 0.05302 -0.0622 0.0165 1.0000
18.250 1.7246 0.06068 0.05485 -0.0609 0.0163 1.0000
18.500 1.7316 0.06246 0.05668 -0.0597 0.0163 1.0000
18.750 1.7376 0.06439 0.05868 -0.0585 0.0162 1.0000
19.000 1.7435 0.06635 0.06071 -0.0574 0.0161 1.0000
19.250 1.7487 0.06841 0.06284 -0.0563 0.0161 1.0000
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