D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 500,000 Max Cl/Cd: 67.37 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1138-il-500000-n5.txt Download as CSV file: xf-dga1138-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: D.G.A. 1138
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5326 0.11282 0.11050 -0.0064 1.0000 0.0062
-11.000 -0.5345 0.10757 0.10527 -0.0085 1.0000 0.0065
-9.500 -0.6981 0.02988 0.02674 -0.0513 1.0000 0.0061
-9.250 -0.6915 0.02419 0.02038 -0.0504 1.0000 0.0064
-9.000 -0.6755 0.02159 0.01736 -0.0492 1.0000 0.0067
-8.750 -0.6570 0.01977 0.01522 -0.0480 1.0000 0.0069
-8.500 -0.6379 0.01817 0.01334 -0.0467 1.0000 0.0075
-8.250 -0.6088 0.01690 0.01180 -0.0475 0.9982 0.0082
-8.000 -0.5785 0.01581 0.01049 -0.0483 0.9962 0.0090
-7.750 -0.5477 0.01485 0.00931 -0.0492 0.9941 0.0100
-7.500 -0.5169 0.01416 0.00853 -0.0500 0.9910 0.0122
-7.250 -0.4844 0.01395 0.00832 -0.0511 0.9880 0.0147
-7.000 -0.4521 0.01380 0.00814 -0.0520 0.9852 0.0170
-6.750 -0.4206 0.01413 0.00849 -0.0527 0.9806 0.0197
-6.500 -0.3883 0.01414 0.00842 -0.0537 0.9772 0.0231
-6.250 -0.3579 0.01411 0.00826 -0.0542 0.9716 0.0249
-6.000 -0.3260 0.01407 0.00813 -0.0551 0.9665 0.0257
-5.750 -0.2960 0.01342 0.00743 -0.0557 0.9594 0.0278
-5.500 -0.2633 0.01329 0.00725 -0.0569 0.9527 0.0295
-5.250 -0.2318 0.01300 0.00687 -0.0577 0.9449 0.0312
-5.000 -0.1999 0.01263 0.00641 -0.0585 0.9381 0.0325
-4.750 -0.1699 0.01213 0.00582 -0.0590 0.9301 0.0330
-4.500 -0.1403 0.01166 0.00526 -0.0593 0.9216 0.0333
-4.000 -0.0845 0.01100 0.00441 -0.0591 0.8980 0.0342
-3.750 -0.0577 0.01061 0.00395 -0.0587 0.8871 0.0342
-3.500 -0.0308 0.01027 0.00354 -0.0584 0.8778 0.0342
-3.250 -0.0039 0.00997 0.00318 -0.0582 0.8687 0.0344
-3.000 0.0232 0.00971 0.00287 -0.0579 0.8596 0.0346
-2.750 0.0504 0.00949 0.00261 -0.0577 0.8509 0.0349
-2.500 0.0776 0.00931 0.00238 -0.0575 0.8405 0.0352
-2.250 0.1044 0.00902 0.00204 -0.0572 0.8277 0.0371
-2.000 0.1317 0.00886 0.00185 -0.0570 0.8150 0.0395
-1.750 0.1589 0.00877 0.00170 -0.0568 0.8005 0.0417
-1.500 0.1859 0.00871 0.00157 -0.0565 0.7837 0.0436
-1.250 0.2126 0.00871 0.00147 -0.0562 0.7595 0.0453
-1.000 0.2391 0.00873 0.00137 -0.0558 0.7341 0.0474
-0.750 0.2655 0.00875 0.00128 -0.0554 0.7049 0.0525
-0.500 0.2918 0.00875 0.00122 -0.0551 0.6685 0.0676
-0.250 0.3144 0.00897 0.00124 -0.0541 0.5624 0.1421
0.000 0.3398 0.00913 0.00134 -0.0538 0.5253 0.1817
0.250 0.3663 0.00918 0.00143 -0.0537 0.5057 0.2202
0.500 0.3932 0.00918 0.00151 -0.0536 0.4918 0.2587
1.000 0.4723 0.00757 0.00179 -0.0595 0.4566 1.0000
1.250 0.4978 0.00774 0.00185 -0.0591 0.4259 1.0000
1.500 0.5214 0.00814 0.00193 -0.0584 0.3493 1.0000
1.750 0.5447 0.00863 0.00211 -0.0577 0.2816 1.0000
2.000 0.5683 0.00909 0.00232 -0.0571 0.2210 1.0000
2.250 0.5927 0.00944 0.00251 -0.0566 0.1880 1.0000
2.500 0.6175 0.00974 0.00270 -0.0561 0.1684 1.0000
2.750 0.6427 0.00998 0.00290 -0.0557 0.1549 1.0000
3.000 0.6684 0.01017 0.00307 -0.0553 0.1476 1.0000
3.250 0.6938 0.01039 0.00325 -0.0550 0.1347 1.0000
3.500 0.7188 0.01067 0.00343 -0.0546 0.1051 1.0000
3.750 0.7423 0.01118 0.00374 -0.0540 0.0735 1.0000
4.000 0.7647 0.01185 0.00417 -0.0532 0.0245 1.0000
4.250 0.7894 0.01222 0.00455 -0.0527 0.0163 1.0000
4.500 0.8139 0.01260 0.00497 -0.0521 0.0135 1.0000
4.750 0.8380 0.01308 0.00555 -0.0515 0.0109 1.0000
5.000 0.8618 0.01359 0.00617 -0.0508 0.0099 1.0000
5.250 0.8859 0.01405 0.00670 -0.0502 0.0093 1.0000
5.500 0.9096 0.01456 0.00727 -0.0495 0.0085 1.0000
5.750 0.9331 0.01505 0.00780 -0.0489 0.0076 1.0000
6.000 0.9558 0.01566 0.00846 -0.0482 0.0070 1.0000
6.250 0.9756 0.01670 0.00961 -0.0470 0.0065 1.0000
6.500 0.9967 0.01753 0.01053 -0.0459 0.0062 1.0000
6.750 1.0178 0.01835 0.01145 -0.0449 0.0059 1.0000
7.000 1.0381 0.01929 0.01250 -0.0438 0.0057 1.0000
7.250 1.0576 0.02036 0.01368 -0.0425 0.0054 1.0000
7.500 1.0770 0.02143 0.01486 -0.0413 0.0052 1.0000
7.750 1.0969 0.02234 0.01587 -0.0403 0.0048 1.0000
8.000 1.1170 0.02311 0.01671 -0.0394 0.0046 1.0000
8.250 1.1357 0.02403 0.01774 -0.0383 0.0043 1.0000
8.500 1.1503 0.02567 0.01950 -0.0367 0.0041 1.0000
8.750 1.1644 0.02745 0.02148 -0.0349 0.0040 1.0000
9.000 1.1786 0.02907 0.02333 -0.0331 0.0039 1.0000
9.250 1.1902 0.03099 0.02550 -0.0310 0.0038 1.0000
9.500 1.1985 0.03322 0.02801 -0.0285 0.0037 1.0000
9.750 1.2025 0.03575 0.03084 -0.0256 0.0036 1.0000
10.000 1.2011 0.03844 0.03382 -0.0222 0.0035 1.0000
10.250 1.1934 0.04103 0.03667 -0.0180 0.0034 1.0000
10.500 1.1828 0.04391 0.03981 -0.0143 0.0034 1.0000
10.750 1.1700 0.04720 0.04334 -0.0115 0.0034 1.0000
11.000 1.1552 0.05099 0.04737 -0.0097 0.0033 1.0000
11.250 1.1388 0.05541 0.05201 -0.0091 0.0033 1.0000
11.500 1.1213 0.06056 0.05737 -0.0100 0.0033 1.0000
11.750 1.1027 0.06671 0.06372 -0.0126 0.0033 1.0000
12.000 1.0841 0.07406 0.07125 -0.0170 0.0034 1.0000
12.250 1.0651 0.08260 0.07996 -0.0228 0.0034 1.0000
12.500 1.0449 0.09229 0.08980 -0.0293 0.0034 1.0000
12.750 1.0242 0.10331 0.10095 -0.0362 0.0035 1.0000
13.000 1.0018 0.11508 0.11281 -0.0425 0.0036 1.0000
13.250 0.9791 0.12648 0.12426 -0.0480 0.0037 1.0000
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Polar data table (+)
Polar graphs
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