Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=1
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Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Reynolds number: 500,000 Max Cl/Cd: 50.76 at α=6.25° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-100-050-gn-500000-n1.txt Download as CSV file: xf-cp-100-050-gn-500000-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 = 0.500 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0624 0.09953 0.09581 -0.1545 0.8822 0.0169
-9.750 0.0730 0.09704 0.09329 -0.1561 0.8777 0.0172
-9.500 0.0841 0.09497 0.09120 -0.1573 0.8731 0.0173
-9.250 0.0949 0.09279 0.08900 -0.1586 0.8679 0.0176
-9.000 0.1064 0.09073 0.08691 -0.1599 0.8630 0.0178
-8.750 0.1164 0.08868 0.08485 -0.1608 0.8580 0.0180
-8.500 0.1263 0.08664 0.08279 -0.1617 0.8530 0.0182
-8.250 0.1362 0.08461 0.08073 -0.1626 0.8471 0.0185
-8.000 0.1454 0.08259 0.07869 -0.1633 0.8423 0.0188
-7.750 0.1530 0.08038 0.07646 -0.1640 0.8370 0.0195
-7.500 0.1616 0.07842 0.07449 -0.1645 0.8315 0.0199
-7.250 0.1713 0.07674 0.07279 -0.1649 0.8263 0.0200
-7.000 0.1797 0.07492 0.07096 -0.1652 0.8206 0.0201
-6.750 0.1883 0.07323 0.06925 -0.1654 0.8147 0.0206
-6.500 0.1960 0.07152 0.06753 -0.1655 0.8092 0.0208
-6.250 0.2031 0.06980 0.06581 -0.1654 0.8039 0.0210
-6.000 0.2095 0.06815 0.06415 -0.1651 0.7982 0.0212
-5.750 0.2134 0.06645 0.06244 -0.1645 0.7927 0.0219
-5.500 0.2140 0.06467 0.06066 -0.1635 0.7862 0.0225
-5.250 0.2213 0.06327 0.05926 -0.1633 0.7810 0.0227
-5.000 0.2298 0.06167 0.05764 -0.1635 0.7756 0.0229
-4.750 0.2399 0.06002 0.05599 -0.1639 0.7701 0.0230
-4.500 0.2508 0.05836 0.05433 -0.1645 0.7647 0.0234
-4.250 0.2623 0.05660 0.05255 -0.1653 0.7596 0.0237
-4.000 0.2751 0.05482 0.05076 -0.1662 0.7544 0.0242
-3.750 0.2887 0.05282 0.04874 -0.1675 0.7492 0.0248
-3.500 0.3036 0.05080 0.04669 -0.1690 0.7441 0.0253
-3.250 0.3201 0.04905 0.04492 -0.1702 0.7394 0.0255
-3.000 0.3383 0.04737 0.04322 -0.1715 0.7345 0.0258
-2.750 0.3573 0.04565 0.04148 -0.1729 0.7296 0.0261
-2.500 0.3772 0.04391 0.03971 -0.1743 0.7250 0.0264
-2.250 0.3970 0.04218 0.03793 -0.1756 0.7172 0.0269
-2.000 0.4173 0.04021 0.03589 -0.1770 0.7074 0.0278
-1.750 0.4328 0.03859 0.03412 -0.1769 0.6864 0.0282
-1.500 0.4483 0.03725 0.03266 -0.1764 0.6645 0.0285
-1.250 0.4564 0.03633 0.03156 -0.1739 0.6306 0.0287
-1.000 0.4535 0.03580 0.03079 -0.1687 0.5824 0.0289
-0.750 0.4174 0.03697 0.03127 -0.1564 0.4274 0.0288
-0.500 0.4030 0.03760 0.03124 -0.1493 0.2535 0.0290
-0.250 0.4014 0.03771 0.03079 -0.1450 0.0384 0.0292
0.000 0.4273 0.03619 0.02919 -0.1462 0.0319 0.0297
0.250 0.4547 0.03455 0.02744 -0.1477 0.0288 0.0306
0.500 0.4830 0.03285 0.02564 -0.1492 0.0273 0.0312
1.000 0.5364 0.03027 0.02288 -0.1508 0.0259 0.0319
1.250 0.5629 0.02910 0.02161 -0.1514 0.0254 0.0324
1.500 0.5898 0.02791 0.02032 -0.1519 0.0251 0.0331
1.750 0.6188 0.02640 0.01865 -0.1527 0.0248 0.0342
2.000 0.6471 0.02499 0.01707 -0.1533 0.0246 0.0348
2.250 0.6730 0.02408 0.01604 -0.1532 0.0244 0.0352
2.500 0.6986 0.02319 0.01501 -0.1529 0.0242 0.0356
2.750 0.7247 0.02212 0.01376 -0.1526 0.0239 0.0365
3.000 0.7534 0.01998 0.01119 -0.1526 0.0238 0.0381
3.250 0.7769 0.01896 0.00988 -0.1517 0.0236 0.0388
3.500 0.7987 0.01844 0.00916 -0.1504 0.0236 0.0396
3.750 0.8201 0.01796 0.00847 -0.1490 0.0232 0.0410
4.000 0.8406 0.01785 0.00825 -0.1474 0.0231 0.0416
4.250 0.8605 0.01792 0.00826 -0.1458 0.0230 0.0418
4.500 0.8802 0.01805 0.00835 -0.1441 0.0229 0.0419
4.750 0.8996 0.01825 0.00854 -0.1424 0.0227 0.0421
5.000 0.9190 0.01848 0.00876 -0.1407 0.0226 0.0423
5.250 0.9379 0.01873 0.00901 -0.1389 0.0225 0.0425
5.500 0.9565 0.01900 0.00928 -0.1371 0.0224 0.0426
5.750 0.9750 0.01930 0.00957 -0.1353 0.0222 0.0431
6.000 0.9934 0.01960 0.00988 -0.1335 0.0221 0.0434
6.250 1.0116 0.01993 0.01021 -0.1317 0.0219 0.0438
6.500 1.0293 0.02029 0.01057 -0.1298 0.0217 0.0440
6.750 1.0469 0.02066 0.01095 -0.1279 0.0214 0.0442
7.000 1.0643 0.02106 0.01136 -0.1260 0.0214 0.0443
7.250 1.0814 0.02149 0.01181 -0.1241 0.0213 0.0446
7.500 1.0981 0.02195 0.01229 -0.1222 0.0212 0.0447
7.750 1.1147 0.02244 0.01279 -0.1202 0.0211 0.0448
8.000 1.1310 0.02295 0.01332 -0.1183 0.0210 0.0452
8.250 1.1471 0.02349 0.01388 -0.1163 0.0210 0.0453
8.500 1.1627 0.02407 0.01448 -0.1144 0.0209 0.0456
8.750 1.1784 0.02467 0.01511 -0.1124 0.0208 0.0456
9.000 1.1937 0.02530 0.01577 -0.1104 0.0208 0.0460
9.250 1.2085 0.02597 0.01648 -0.1084 0.0207 0.0461
9.500 1.2232 0.02666 0.01721 -0.1065 0.0207 0.0464
9.750 1.2379 0.02737 0.01796 -0.1045 0.0207 0.0467
10.000 1.2521 0.02814 0.01878 -0.1025 0.0205 0.0477
10.250 1.2662 0.02892 0.01960 -0.1006 0.0205 0.0482
10.500 1.2800 0.02974 0.02047 -0.0987 0.0204 0.0487
10.750 1.2938 0.03058 0.02135 -0.0968 0.0201 0.0491
11.000 1.3069 0.03148 0.02230 -0.0948 0.0200 0.0494
11.250 1.3204 0.03239 0.02326 -0.0930 0.0198 0.0500
11.500 1.3336 0.03333 0.02426 -0.0911 0.0195 0.0504
11.750 1.3464 0.03431 0.02529 -0.0893 0.0194 0.0509
12.000 1.3592 0.03532 0.02635 -0.0875 0.0193 0.0516
12.250 1.3722 0.03633 0.02742 -0.0858 0.0191 0.0531
12.500 1.3844 0.03743 0.02859 -0.0840 0.0191 0.0569
12.750 1.3971 0.03847 0.02979 -0.0823 0.0188 0.1454
13.500 1.4614 0.04174 0.03424 -0.0834 0.0185 1.0000
13.750 1.4730 0.04295 0.03550 -0.0818 0.0183 1.0000
14.000 1.4849 0.04416 0.03676 -0.0801 0.0182 1.0000
14.250 1.4963 0.04542 0.03807 -0.0785 0.0181 1.0000
14.500 1.5075 0.04671 0.03941 -0.0769 0.0180 1.0000
14.750 1.5186 0.04802 0.04077 -0.0754 0.0179 1.0000
15.000 1.5298 0.04933 0.04214 -0.0739 0.0179 1.0000
15.250 1.5404 0.05071 0.04358 -0.0724 0.0177 1.0000
15.500 1.5509 0.05212 0.04505 -0.0709 0.0176 1.0000
15.750 1.5613 0.05356 0.04654 -0.0695 0.0176 1.0000
16.000 1.5709 0.05512 0.04819 -0.0681 0.0174 1.0000
16.250 1.5801 0.05675 0.04992 -0.0666 0.0172 1.0000
16.500 1.5893 0.05837 0.05163 -0.0652 0.0170 1.0000
16.750 1.5982 0.06009 0.05345 -0.0639 0.0169 1.0000
17.000 1.6064 0.06190 0.05536 -0.0626 0.0167 1.0000
17.250 1.6138 0.06382 0.05739 -0.0613 0.0166 1.0000
17.500 1.6207 0.06579 0.05948 -0.0601 0.0165 1.0000
17.750 1.6268 0.06791 0.06171 -0.0589 0.0164 1.0000
18.000 1.6316 0.07020 0.06413 -0.0579 0.0162 1.0000
18.250 1.6358 0.07260 0.06667 -0.0569 0.0161 1.0000
18.500 1.6386 0.07519 0.06938 -0.0560 0.0160 1.0000
18.750 1.6402 0.07798 0.07232 -0.0552 0.0158 1.0000
19.000 1.6400 0.08103 0.07552 -0.0545 0.0157 1.0000
19.250 1.6385 0.08431 0.07896 -0.0540 0.0156 1.0000
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