D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: D.G.A. 1182 (dga1182-il) Reynolds number: 1,000,000 Max Cl/Cd: 55.69 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1182-il-1000000-n5.txt Download as CSV file: xf-dga1182-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6335 0.09289 0.08928 0.0106 0.1246 0.0017
-8.250 -0.6347 0.08784 0.08426 0.0069 0.1246 0.0017
-8.000 -0.6380 0.08239 0.07883 0.0012 0.1246 0.0017
-7.750 -0.6375 0.07599 0.07241 -0.0060 0.1246 0.0017
-7.500 -0.6339 0.06928 0.06562 -0.0119 0.1245 0.0016
-7.250 -0.6287 0.06365 0.05986 -0.0151 0.1245 0.0016
-7.000 -0.6208 0.05822 0.05428 -0.0172 0.1244 0.0016
-6.750 -0.6104 0.05273 0.04859 -0.0183 0.1244 0.0016
-6.500 -0.5978 0.04666 0.04227 -0.0187 0.1244 0.0016
-6.250 -0.5843 0.03851 0.03372 -0.0180 0.1243 0.0019
-6.000 -0.5641 0.03437 0.02932 -0.0174 0.1243 0.0021
-5.750 -0.5448 0.02930 0.02385 -0.0164 0.1242 0.0023
-5.500 -0.5214 0.02737 0.02171 -0.0161 0.1242 0.0025
-5.250 -0.4974 0.02552 0.01964 -0.0157 0.1242 0.0027
-5.000 -0.4729 0.02344 0.01731 -0.0152 0.1242 0.0030
-4.750 -0.4478 0.02110 0.01466 -0.0144 0.1242 0.0034
-4.500 -0.4211 0.01840 0.01151 -0.0132 0.1241 0.0051
-4.250 -0.3937 0.01842 0.01141 -0.0131 0.1232 0.0055
-4.000 -0.3690 0.01645 0.00927 -0.0129 0.1224 0.0062
-3.750 -0.3426 0.01614 0.00893 -0.0129 0.1219 0.0067
-3.500 -0.3160 0.01560 0.00833 -0.0129 0.1218 0.0072
-3.250 -0.2893 0.01504 0.00770 -0.0128 0.1218 0.0077
-3.000 -0.2625 0.01448 0.00702 -0.0126 0.1216 0.0083
-2.750 -0.2359 0.01369 0.00614 -0.0123 0.1215 0.0082
-2.500 -0.2094 0.01304 0.00540 -0.0120 0.1214 0.0082
-2.250 -0.1826 0.01251 0.00480 -0.0118 0.1213 0.0085
-2.000 -0.1555 0.01215 0.00436 -0.0117 0.1211 0.0097
-1.750 -0.1280 0.01205 0.00424 -0.0117 0.1209 0.0116
-1.500 -0.1001 0.01211 0.00428 -0.0118 0.1204 0.0126
-1.250 -0.0732 0.01164 0.00375 -0.0118 0.1196 0.0149
-1.000 -0.0456 0.01145 0.00350 -0.0118 0.1189 0.0155
-0.750 -0.0180 0.01130 0.00332 -0.0119 0.1183 0.0164
-0.500 0.0097 0.01116 0.00316 -0.0119 0.1173 0.0182
-0.250 0.0377 0.01103 0.00298 -0.0120 0.1159 0.0178
0.000 0.0659 0.01089 0.00279 -0.0120 0.1145 0.0171
0.250 0.0949 0.01057 0.00242 -0.0121 0.1126 0.0164
0.500 0.1220 0.01070 0.00254 -0.0122 0.1087 0.0159
0.750 0.1496 0.01074 0.00256 -0.0122 0.0897 0.0154
1.000 0.1790 0.01034 0.00203 -0.0124 0.0843 0.0150
1.250 0.2069 0.01033 0.00198 -0.0124 0.0778 0.0147
1.500 0.2346 0.01038 0.00202 -0.0125 0.0755 0.0146
1.750 0.2624 0.01044 0.00205 -0.0126 0.0733 0.0148
2.000 0.2901 0.01050 0.00210 -0.0127 0.0699 0.0161
2.250 0.3174 0.01027 0.00220 -0.0128 0.0662 0.1839
2.500 0.3444 0.01001 0.00229 -0.0129 0.0650 0.3335
2.750 0.3721 0.01016 0.00250 -0.0130 0.0616 0.3515
3.000 0.3996 0.01031 0.00261 -0.0131 0.0514 0.3533
3.250 0.4265 0.01057 0.00277 -0.0132 0.0352 0.3548
3.500 0.4540 0.01073 0.00293 -0.0132 0.0318 0.3560
3.750 0.4813 0.01090 0.00314 -0.0133 0.0303 0.3571
4.000 0.5086 0.01107 0.00332 -0.0133 0.0290 0.3581
4.250 0.5355 0.01132 0.00353 -0.0133 0.0241 0.3589
4.500 0.5627 0.01148 0.00370 -0.0134 0.0222 0.3598
4.750 0.5899 0.01164 0.00387 -0.0134 0.0208 0.3607
5.000 0.6159 0.01207 0.00417 -0.0134 0.0038 0.3613
5.250 0.6429 0.01231 0.00445 -0.0133 0.0029 0.3618
5.500 0.6697 0.01257 0.00475 -0.0133 0.0026 0.3622
5.750 0.6965 0.01284 0.00513 -0.0132 0.0025 0.3629
6.000 0.7231 0.01314 0.00551 -0.0131 0.0025 0.3637
6.250 0.7495 0.01350 0.00594 -0.0130 0.0024 0.3645
6.500 0.7757 0.01393 0.00644 -0.0129 0.0023 0.3652
6.750 0.8014 0.01443 0.00704 -0.0127 0.0021 0.3662
7.000 0.8269 0.01503 0.00773 -0.0126 0.0018 0.3672
7.250 0.8523 0.01571 0.00850 -0.0124 0.0017 0.3682
7.500 0.8774 0.01645 0.00936 -0.0121 0.0016 0.3689
7.750 0.9021 0.01732 0.01035 -0.0118 0.0015 0.3696
8.000 0.9263 0.01829 0.01154 -0.0115 0.0015 0.3705
8.250 0.9491 0.01966 0.01313 -0.0110 0.0013 0.3715
8.500 0.9661 0.02263 0.01660 -0.0097 0.0011 0.3724
8.750 0.9900 0.02361 0.01771 -0.0095 0.0011 0.3734
9.000 1.0136 0.02464 0.01888 -0.0092 0.0010 0.3741
9.250 1.0357 0.02605 0.02048 -0.0088 0.0010 0.3745
9.500 1.0563 0.02776 0.02242 -0.0083 0.0009 0.3749
9.750 1.0742 0.03006 0.02499 -0.0076 0.0009 0.3753
10.000 1.0886 0.03323 0.02850 -0.0066 0.0008 0.3755
10.250 1.0964 0.03760 0.03328 -0.0052 0.0008 0.3761
10.500 1.0925 0.04421 0.04036 -0.0036 0.0007 0.3764
10.750 1.0769 0.05191 0.04846 -0.0020 0.0008 0.3765
11.000 1.0518 0.05925 0.05610 -0.0012 0.0008 0.3764
11.250 1.0226 0.06493 0.06193 -0.0007 0.0008 0.3764
11.500 0.9896 0.07204 0.06915 -0.0054 0.0008 0.3762
11.750 0.9334 0.09302 0.09007 -0.0253 0.0010 0.3754
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Polar data table (+)
Polar graphs
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