D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: D.G.A. 1182 (dga1182-il) Reynolds number: 500,000 Max Cl/Cd: 47.57 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1182-il-500000-n5.txt Download as CSV file: xf-dga1182-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: D.G.A. 1182
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6197 0.09215 0.08801 0.0084 0.1350 0.0036
-8.000 -0.6202 0.08716 0.08305 0.0045 0.1350 0.0035
-7.750 -0.6233 0.08177 0.07768 -0.0014 0.1349 0.0034
-7.500 -0.6201 0.07554 0.07140 -0.0077 0.1349 0.0033
-7.250 -0.6154 0.06927 0.06504 -0.0128 0.1349 0.0032
-7.000 -0.6088 0.06385 0.05948 -0.0158 0.1348 0.0031
-6.750 -0.5993 0.05873 0.05418 -0.0177 0.1348 0.0031
-6.500 -0.5869 0.05386 0.04911 -0.0189 0.1348 0.0030
-6.250 -0.5719 0.04926 0.04428 -0.0194 0.1347 0.0031
-6.000 -0.5544 0.04487 0.03964 -0.0195 0.1347 0.0032
-5.750 -0.5348 0.04052 0.03500 -0.0192 0.1347 0.0035
-5.500 -0.5135 0.03593 0.03007 -0.0184 0.1347 0.0040
-5.250 -0.4904 0.03119 0.02490 -0.0171 0.1347 0.0046
-5.000 -0.4433 0.01484 0.00847 -0.0169 0.1351 0.0057
-4.750 -0.4428 0.02555 0.01849 -0.0156 0.1348 0.0062
-4.500 -0.4185 0.02359 0.01626 -0.0152 0.1350 0.0064
-4.250 -0.3933 0.02208 0.01454 -0.0148 0.1351 0.0068
-4.000 -0.3675 0.02084 0.01311 -0.0146 0.1353 0.0074
-3.750 -0.3411 0.01972 0.01179 -0.0142 0.1355 0.0086
-3.500 -0.3144 0.01870 0.01058 -0.0139 0.1351 0.0096
-3.250 -0.2874 0.01815 0.00987 -0.0136 0.1341 0.0112
-3.000 -0.2609 0.01720 0.00871 -0.0132 0.1328 0.0112
-2.750 -0.2347 0.01646 0.00783 -0.0129 0.1319 0.0112
-2.500 -0.2085 0.01582 0.00708 -0.0125 0.1317 0.0114
-2.250 -0.1820 0.01529 0.00645 -0.0123 0.1316 0.0118
-2.000 -0.1550 0.01504 0.00613 -0.0121 0.1315 0.0126
-1.750 -0.1292 0.01427 0.00530 -0.0119 0.1314 0.0147
-1.500 -0.1024 0.01393 0.00492 -0.0119 0.1312 0.0165
-1.250 -0.0751 0.01365 0.00460 -0.0118 0.1306 0.0178
-1.000 -0.0476 0.01346 0.00435 -0.0119 0.1297 0.0196
-0.750 -0.0202 0.01333 0.00415 -0.0118 0.1292 0.0198
-0.500 0.0073 0.01323 0.00398 -0.0118 0.1285 0.0195
-0.250 0.0348 0.01319 0.00387 -0.0118 0.1278 0.0192
0.000 0.0624 0.01318 0.00380 -0.0118 0.1269 0.0189
0.250 0.0900 0.01318 0.00373 -0.0118 0.1256 0.0186
0.500 0.1177 0.01318 0.00369 -0.0118 0.1240 0.0184
0.750 0.1454 0.01319 0.00368 -0.0119 0.1226 0.0183
1.000 0.1732 0.01315 0.00364 -0.0119 0.1208 0.0183
1.250 0.2012 0.01299 0.00352 -0.0120 0.1165 0.0186
1.500 0.2298 0.01277 0.00332 -0.0121 0.1122 0.0197
1.750 0.2563 0.01263 0.00350 -0.0121 0.1086 0.1777
2.000 0.2830 0.01268 0.00364 -0.0121 0.0897 0.2147
2.250 0.3121 0.01213 0.00334 -0.0124 0.0853 0.3458
2.500 0.3413 0.01222 0.00346 -0.0125 0.0782 0.3680
2.750 0.3685 0.01237 0.00362 -0.0126 0.0751 0.3691
3.000 0.3958 0.01251 0.00376 -0.0126 0.0709 0.3700
3.250 0.4232 0.01264 0.00389 -0.0126 0.0659 0.3709
3.500 0.4501 0.01283 0.00412 -0.0126 0.0604 0.3717
3.750 0.4771 0.01303 0.00430 -0.0126 0.0470 0.3725
4.000 0.5042 0.01322 0.00442 -0.0126 0.0391 0.3733
4.250 0.5315 0.01338 0.00457 -0.0126 0.0357 0.3743
4.500 0.5589 0.01354 0.00477 -0.0126 0.0336 0.3750
4.750 0.5857 0.01372 0.00499 -0.0126 0.0317 0.3755
5.000 0.6119 0.01397 0.00521 -0.0126 0.0258 0.3761
5.250 0.6384 0.01418 0.00543 -0.0126 0.0213 0.3769
5.500 0.6641 0.01460 0.00570 -0.0125 0.0054 0.3779
5.750 0.6907 0.01490 0.00613 -0.0124 0.0040 0.3789
6.000 0.7169 0.01526 0.00660 -0.0122 0.0038 0.3798
6.250 0.7429 0.01568 0.00713 -0.0120 0.0037 0.3805
6.500 0.7687 0.01616 0.00772 -0.0118 0.0036 0.3812
6.750 0.7943 0.01670 0.00840 -0.0115 0.0035 0.3820
7.000 0.8197 0.01733 0.00918 -0.0113 0.0035 0.3832
7.250 0.8448 0.01804 0.01006 -0.0109 0.0034 0.3846
7.500 0.8695 0.01886 0.01104 -0.0106 0.0032 0.3859
7.750 0.8938 0.01976 0.01212 -0.0103 0.0029 0.3868
8.000 0.9178 0.02077 0.01330 -0.0099 0.0026 0.3875
8.250 0.9413 0.02190 0.01472 -0.0095 0.0024 0.3880
8.500 0.9639 0.02325 0.01632 -0.0090 0.0023 0.3885
8.750 0.9855 0.02487 0.01821 -0.0084 0.0022 0.3889
9.000 1.0060 0.02675 0.02040 -0.0078 0.0021 0.3897
9.250 1.0247 0.02902 0.02301 -0.0070 0.0019 0.3904
9.500 1.0406 0.03188 0.02628 -0.0061 0.0018 0.3911
9.750 1.0528 0.03545 0.03027 -0.0050 0.0017 0.3917
10.000 1.0588 0.04016 0.03544 -0.0037 0.0017 0.3922
10.250 1.0542 0.04663 0.04241 -0.0023 0.0016 0.3925
10.500 1.0360 0.05467 0.05090 -0.0011 0.0017 0.3925
10.750 1.0059 0.06262 0.05917 -0.0009 0.0017 0.3923
11.000 0.9702 0.06935 0.06604 -0.0024 0.0018 0.3921
11.250 0.9161 0.08803 0.08476 -0.0203 0.0021 0.3911
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Polar data table (+)
Polar graphs
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