Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=1
| Details | Polar file |
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Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Reynolds number: 500,000 Max Cl/Cd: 46.05 at α=5.75° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-120-050-gn-500000-n1.txt Download as CSV file: xf-cp-120-050-gn-500000-n1.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=12% T=5% R=1.1
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
------ -------- --------- --------- -------- -------- --------
-11.500 0.1622 0.10648 0.10258 -0.1837 0.8608 0.0119
-11.250 0.1715 0.10426 0.10034 -0.1848 0.8573 0.0121
-11.000 0.1804 0.10192 0.09798 -0.1859 0.8536 0.0125
-10.750 0.1899 0.09987 0.09591 -0.1869 0.8499 0.0125
-10.500 0.1996 0.09797 0.09399 -0.1877 0.8450 0.0128
-10.250 0.2090 0.09596 0.09196 -0.1885 0.8410 0.0129
-10.000 0.2187 0.09410 0.09008 -0.1893 0.8373 0.0130
-9.750 0.2278 0.09218 0.08814 -0.1900 0.8329 0.0134
-9.500 0.2367 0.09029 0.08623 -0.1905 0.8284 0.0136
-9.250 0.2451 0.08830 0.08423 -0.1911 0.8242 0.0141
-9.000 0.2532 0.08634 0.08225 -0.1916 0.8203 0.0146
-8.750 0.2616 0.08449 0.08038 -0.1920 0.8161 0.0147
-8.500 0.2702 0.08274 0.07862 -0.1922 0.8112 0.0149
-8.250 0.2789 0.08108 0.07695 -0.1925 0.8069 0.0149
-8.000 0.2874 0.07946 0.07531 -0.1926 0.8030 0.0153
-7.750 0.2957 0.07783 0.07368 -0.1927 0.7985 0.0155
-7.500 0.3034 0.07620 0.07204 -0.1926 0.7934 0.0157
-7.250 0.3105 0.07459 0.07042 -0.1924 0.7891 0.0162
-7.000 0.3166 0.07291 0.06873 -0.1920 0.7849 0.0167
-6.750 0.3223 0.07128 0.06709 -0.1916 0.7802 0.0170
-6.500 0.3274 0.06979 0.06560 -0.1908 0.7748 0.0172
-6.250 0.3325 0.06850 0.06432 -0.1898 0.7709 0.0173
-6.000 0.3361 0.06727 0.06310 -0.1884 0.7664 0.0175
-5.750 0.3382 0.06610 0.06193 -0.1867 0.7614 0.0177
-5.500 0.3430 0.06482 0.06065 -0.1857 0.7562 0.0179
-5.250 0.3492 0.06341 0.05923 -0.1851 0.7520 0.0183
-5.000 0.3563 0.06192 0.05775 -0.1848 0.7477 0.0187
-4.750 0.3633 0.06041 0.05623 -0.1844 0.7426 0.0192
-4.500 0.3706 0.05890 0.05471 -0.1840 0.7379 0.0195
-4.250 0.3791 0.05744 0.05325 -0.1837 0.7340 0.0196
-4.000 0.3865 0.05599 0.05181 -0.1830 0.7293 0.0197
-3.750 0.3939 0.05470 0.05051 -0.1821 0.7241 0.0199
-3.500 0.4030 0.05333 0.04914 -0.1815 0.7200 0.0201
-3.250 0.4149 0.05184 0.04764 -0.1815 0.7164 0.0204
-3.000 0.4281 0.05029 0.04608 -0.1818 0.7117 0.0209
-2.750 0.4418 0.04866 0.04444 -0.1822 0.7067 0.0215
-2.500 0.4577 0.04700 0.04275 -0.1830 0.7026 0.0219
-2.250 0.4768 0.04533 0.04107 -0.1843 0.6992 0.0221
-2.000 0.4974 0.04360 0.03931 -0.1859 0.6946 0.0224
-1.750 0.5186 0.04200 0.03769 -0.1874 0.6900 0.0227
-1.500 0.5409 0.04048 0.03613 -0.1889 0.6861 0.0230
-1.250 0.5659 0.03888 0.03451 -0.1909 0.6825 0.0235
-1.000 0.5936 0.03711 0.03271 -0.1935 0.6785 0.0244
-0.750 0.6217 0.03546 0.03101 -0.1960 0.6740 0.0248
-0.500 0.6454 0.03401 0.02948 -0.1973 0.6645 0.0251
-0.250 0.6667 0.03276 0.02813 -0.1978 0.6503 0.0254
0.000 0.6805 0.03198 0.02722 -0.1965 0.6249 0.0256
0.250 0.6887 0.03147 0.02651 -0.1939 0.5916 0.0259
0.500 0.6837 0.03167 0.02639 -0.1885 0.5314 0.0262
0.750 0.6522 0.03357 0.02760 -0.1782 0.3869 0.0262
1.000 0.6444 0.03473 0.02817 -0.1730 0.2447 0.0266
1.250 0.6441 0.03568 0.02852 -0.1694 0.0286 0.0271
1.750 0.7089 0.03343 0.02606 -0.1741 0.0210 0.0280
2.250 0.7692 0.03161 0.02408 -0.1773 0.0197 0.0287
2.500 0.7982 0.03081 0.02319 -0.1784 0.0194 0.0294
2.750 0.8279 0.02994 0.02221 -0.1796 0.0190 0.0304
3.000 0.8566 0.02915 0.02132 -0.1805 0.0189 0.0308
3.250 0.8848 0.02836 0.02042 -0.1812 0.0186 0.0313
3.750 0.9365 0.02718 0.01902 -0.1813 0.0181 0.0320
4.000 0.9622 0.02655 0.01826 -0.1812 0.0179 0.0333
4.250 0.9879 0.02587 0.01741 -0.1810 0.0178 0.0338
4.500 1.0157 0.02470 0.01593 -0.1810 0.0177 0.0347
4.750 1.0391 0.02410 0.01508 -0.1802 0.0176 0.0353
5.000 1.0616 0.02347 0.01411 -0.1792 0.0174 0.0372
5.250 1.0805 0.02357 0.01407 -0.1777 0.0173 0.0377
5.500 1.0985 0.02387 0.01432 -0.1760 0.0171 0.0379
5.750 1.1162 0.02424 0.01464 -0.1744 0.0171 0.0382
6.000 1.1337 0.02465 0.01503 -0.1727 0.0170 0.0384
6.250 1.1503 0.02518 0.01557 -0.1709 0.0169 0.0385
6.500 1.1667 0.02574 0.01614 -0.1691 0.0169 0.0388
6.750 1.1830 0.02631 0.01672 -0.1673 0.0167 0.0392
7.000 1.1993 0.02689 0.01731 -0.1655 0.0167 0.0394
7.250 1.2149 0.02752 0.01796 -0.1636 0.0165 0.0396
7.500 1.2300 0.02821 0.01866 -0.1617 0.0165 0.0397
7.750 1.2455 0.02889 0.01936 -0.1599 0.0163 0.0399
8.000 1.2607 0.02960 0.02009 -0.1581 0.0162 0.0400
8.250 1.2752 0.03038 0.02089 -0.1562 0.0160 0.0402
8.500 1.2897 0.03119 0.02172 -0.1544 0.0159 0.0403
8.750 1.3039 0.03202 0.02258 -0.1525 0.0158 0.0405
9.000 1.3177 0.03292 0.02350 -0.1506 0.0157 0.0407
9.250 1.3311 0.03385 0.02447 -0.1487 0.0157 0.0408
9.500 1.3443 0.03482 0.02548 -0.1469 0.0156 0.0411
9.750 1.3575 0.03581 0.02651 -0.1450 0.0156 0.0414
10.000 1.3699 0.03689 0.02762 -0.1432 0.0155 0.0416
10.250 1.3824 0.03799 0.02877 -0.1413 0.0155 0.0417
10.500 1.3948 0.03910 0.02993 -0.1395 0.0154 0.0420
10.750 1.4062 0.04033 0.03121 -0.1377 0.0154 0.0426
11.000 1.4180 0.04154 0.03247 -0.1359 0.0153 0.0437
11.250 1.4293 0.04281 0.03381 -0.1341 0.0153 0.0448
11.500 1.4402 0.04414 0.03519 -0.1324 0.0152 0.0454
11.750 1.4514 0.04548 0.03658 -0.1307 0.0151 0.0457
12.000 1.4620 0.04689 0.03805 -0.1290 0.0151 0.0464
12.250 1.4723 0.04834 0.03956 -0.1273 0.0150 0.0474
12.500 1.4828 0.04979 0.04108 -0.1257 0.0148 0.0487
12.750 1.4932 0.05129 0.04265 -0.1241 0.0147 0.0541
13.500 1.5399 0.05592 0.04843 -0.1233 0.0140 1.0000
13.750 1.5488 0.05758 0.05013 -0.1217 0.0139 1.0000
14.000 1.5582 0.05919 0.05180 -0.1201 0.0137 1.0000
14.250 1.5674 0.06082 0.05348 -0.1186 0.0136 1.0000
14.500 1.5765 0.06250 0.05523 -0.1171 0.0135 1.0000
14.750 1.5858 0.06417 0.05695 -0.1157 0.0134 1.0000
15.000 1.5951 0.06584 0.05868 -0.1143 0.0133 1.0000
15.250 1.6045 0.06751 0.06040 -0.1130 0.0132 1.0000
15.500 1.6135 0.06923 0.06219 -0.1117 0.0131 1.0000
15.750 1.6226 0.07096 0.06399 -0.1104 0.0130 1.0000
16.000 1.6318 0.07267 0.06577 -0.1092 0.0129 1.0000
16.250 1.6409 0.07442 0.06758 -0.1080 0.0128 1.0000
16.500 1.6495 0.07625 0.06949 -0.1069 0.0127 1.0000
16.750 1.6580 0.07809 0.07140 -0.1058 0.0127 1.0000
17.000 1.6665 0.07993 0.07332 -0.1047 0.0126 1.0000
17.250 1.6748 0.08180 0.07529 -0.1036 0.0125 1.0000
17.500 1.6825 0.08376 0.07734 -0.1025 0.0125 1.0000
17.750 1.6901 0.08575 0.07945 -0.1015 0.0124 1.0000
18.000 1.6976 0.08777 0.08160 -0.1005 0.0122 1.0000
18.250 1.7049 0.08985 0.08382 -0.0995 0.0120 1.0000
18.500 1.7114 0.09206 0.08618 -0.0986 0.0117 1.0000
18.750 1.7163 0.09449 0.08876 -0.0978 0.0115 1.0000
19.000 1.7198 0.09712 0.09154 -0.0971 0.0114 1.0000
19.250 1.7221 0.09994 0.09453 -0.0965 0.0113 1.0000
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Polar data table (+)
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