D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: D.G.A. 1182 (dga1182-il) Reynolds number: 100,000 Max Cl/Cd: 27.84 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1182-il-100000-n5.txt Download as CSV file: xf-dga1182-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6253 0.10342 0.09731 0.0011 0.3092 0.0402
-8.500 -0.6267 0.09823 0.09214 -0.0054 0.3086 0.0403
-8.250 -0.6298 0.09379 0.08762 -0.0102 0.3079 0.0404
-8.000 -0.6297 0.08976 0.08345 -0.0135 0.3068 0.0406
-7.750 -0.6209 0.08404 0.07795 -0.0087 0.3018 0.0431
-7.500 -0.6157 0.07990 0.07378 -0.0105 0.2991 0.0446
-7.250 -0.6103 0.07540 0.06919 -0.0133 0.2970 0.0461
-7.000 -0.6035 0.07094 0.06459 -0.0159 0.2952 0.0480
-6.750 -0.5419 0.05266 0.04647 -0.0224 0.2952 0.0559
-6.500 -0.5335 0.04831 0.04205 -0.0225 0.2932 0.0580
-6.250 -0.5245 0.04387 0.03743 -0.0230 0.2916 0.0605
-6.000 -0.5161 0.03916 0.03235 -0.0239 0.2906 0.0697
-5.750 -0.5297 0.04768 0.03983 -0.0210 0.2869 0.0276
-5.500 -0.5104 0.04367 0.03543 -0.0209 0.2849 0.0249
-5.250 -0.4877 0.03944 0.03067 -0.0202 0.2828 0.0222
-5.000 -0.4614 0.03630 0.02683 -0.0190 0.2806 0.0201
-4.750 -0.4360 0.03432 0.02442 -0.0183 0.2782 0.0196
-4.500 -0.4119 0.03141 0.02108 -0.0177 0.2761 0.0197
-4.250 -0.3883 0.02837 0.01772 -0.0174 0.2743 0.0212
-4.000 -0.3626 0.02641 0.01552 -0.0170 0.2724 0.0227
-3.750 -0.3356 0.02453 0.01335 -0.0163 0.2703 0.0229
-3.500 -0.3090 0.02289 0.01148 -0.0156 0.2684 0.0234
-3.250 -0.2830 0.02148 0.00995 -0.0149 0.2664 0.0243
-3.000 -0.2578 0.02040 0.00880 -0.0141 0.2645 0.0269
-2.750 -0.2324 0.01961 0.00785 -0.0134 0.2626 0.0300
-2.500 -0.2072 0.01868 0.00674 -0.0129 0.2608 0.0325
-2.250 -0.1804 0.01809 0.00598 -0.0126 0.2601 0.0387
-1.750 -0.1269 0.01649 0.00519 -0.0124 0.2590 0.3585
-1.500 -0.1005 0.01675 0.00519 -0.0121 0.2590 0.4224
-1.250 -0.0737 0.01653 0.00486 -0.0119 0.2590 0.4371
-1.000 -0.0457 0.01635 0.00465 -0.0118 0.2115 0.4400
-0.750 -0.0188 0.01638 0.00442 -0.0118 0.2042 0.4426
-0.500 0.0085 0.01634 0.00422 -0.0117 0.2029 0.4446
-0.250 0.0359 0.01631 0.00408 -0.0116 0.2019 0.4457
0.000 0.0632 0.01631 0.00393 -0.0115 0.1980 0.4474
0.250 0.0904 0.01636 0.00385 -0.0115 0.1934 0.4490
0.500 0.1174 0.01652 0.00392 -0.0114 0.1892 0.4501
0.750 0.1441 0.01676 0.00408 -0.0113 0.1839 0.4508
1.000 0.1708 0.01698 0.00430 -0.0112 0.1791 0.4514
1.250 0.1973 0.01723 0.00454 -0.0110 0.1759 0.4526
1.500 0.2237 0.01744 0.00477 -0.0109 0.1742 0.4542
1.750 0.2499 0.01764 0.00502 -0.0107 0.1725 0.4561
2.000 0.2764 0.01782 0.00528 -0.0105 0.1706 0.4576
2.250 0.3023 0.01816 0.00566 -0.0103 0.1674 0.4589
2.500 0.3271 0.01880 0.00626 -0.0100 0.1636 0.4603
2.750 0.3527 0.01929 0.00682 -0.0097 0.1589 0.4622
3.000 0.3777 0.02023 0.00768 -0.0095 0.1491 0.4645
3.250 0.4035 0.02087 0.00839 -0.0093 0.1368 0.4671
3.500 0.4298 0.02112 0.00885 -0.0092 0.1265 0.4697
3.750 0.4564 0.02113 0.00919 -0.0090 0.1162 0.4723
4.000 0.4835 0.02118 0.00952 -0.0088 0.1048 0.4744
4.250 0.5102 0.02135 0.00987 -0.0086 0.0951 0.4761
4.500 0.5370 0.02137 0.01008 -0.0085 0.0891 0.4780
4.750 0.5637 0.02148 0.01035 -0.0084 0.0838 0.4803
5.250 0.6151 0.02277 0.01186 -0.0078 0.0761 0.4879
5.500 0.6407 0.02395 0.01322 -0.0074 0.0732 0.4947
6.000 0.6830 0.02453 0.01512 -0.0049 0.0662 0.8473
6.250 0.7100 0.02618 0.01724 -0.0046 0.0628 0.9017
6.500 0.7408 0.02820 0.01974 -0.0054 0.0589 1.0000
6.750 0.7641 0.02911 0.02082 -0.0050 0.0549 1.0000
7.000 0.7872 0.03010 0.02217 -0.0045 0.0459 1.0000
7.250 0.8093 0.03088 0.02323 -0.0041 0.0390 1.0000
7.500 0.8310 0.03157 0.02408 -0.0036 0.0324 1.0000
7.750 0.8470 0.03656 0.02986 -0.0023 0.0271 1.0000
8.000 0.8603 0.04105 0.03495 -0.0012 0.0232 1.0000
8.250 0.8740 0.04387 0.03810 -0.0004 0.0213 1.0000
8.750 0.8821 0.05308 0.04806 0.0013 0.0194 1.0000
9.000 0.8743 0.05978 0.05519 0.0016 0.0191 1.0000
9.250 0.8627 0.06597 0.06166 0.0012 0.0190 1.0000
9.500 0.8482 0.07150 0.06736 0.0002 0.0190 1.0000
9.750 0.8314 0.07675 0.07270 -0.0020 0.0192 1.0000
10.000 0.8168 0.08325 0.07925 -0.0074 0.0195 1.0000
10.250 0.8058 0.09133 0.08730 -0.0142 0.0198 1.0000
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Polar data table (+)
Polar graphs
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