D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 200,000 Max Cl/Cd: 57.38 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1138-il-200000-n5.txt Download as CSV file: xf-dga1138-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5136 0.08860 0.08512 -0.0193 1.0000 0.0136
-9.250 -0.5217 0.08311 0.07970 -0.0223 1.0000 0.0139
-9.000 -0.5266 0.07847 0.07513 -0.0254 1.0000 0.0143
-8.750 -0.5155 0.07758 0.07423 -0.0259 1.0000 0.0154
-8.500 -0.5118 0.07354 0.07021 -0.0288 1.0000 0.0160
-8.250 -0.5093 0.06827 0.06492 -0.0325 1.0000 0.0165
-8.000 -0.5060 0.06214 0.05875 -0.0363 1.0000 0.0172
-7.750 -0.5015 0.05464 0.05111 -0.0401 1.0000 0.0180
-7.500 -0.5030 0.03925 0.03511 -0.0451 1.0000 0.0193
-7.250 -0.4931 0.03393 0.02926 -0.0451 1.0000 0.0215
-7.000 -0.4731 0.03498 0.03045 -0.0439 1.0000 0.0234
-6.750 -0.4592 0.03178 0.02685 -0.0428 1.0000 0.0250
-6.500 -0.4442 0.02864 0.02321 -0.0414 0.9999 0.0264
-6.250 -0.4130 0.02597 0.01994 -0.0429 0.9968 0.0281
-6.000 -0.3790 0.02536 0.01890 -0.0442 0.9936 0.0298
-5.750 -0.3495 0.02241 0.01546 -0.0453 0.9899 0.0304
-5.500 -0.3185 0.02017 0.01286 -0.0464 0.9869 0.0312
-5.250 -0.2878 0.01875 0.01124 -0.0473 0.9834 0.0323
-5.000 -0.2567 0.01772 0.00998 -0.0481 0.9795 0.0338
-4.750 -0.2237 0.01683 0.00894 -0.0493 0.9764 0.0357
-4.500 -0.1926 0.01606 0.00804 -0.0499 0.9713 0.0378
-4.250 -0.1597 0.01538 0.00725 -0.0510 0.9670 0.0398
-4.000 -0.1266 0.01493 0.00669 -0.0521 0.9630 0.0422
-3.750 -0.0966 0.01426 0.00600 -0.0527 0.9575 0.0450
-3.500 -0.0647 0.01359 0.00535 -0.0537 0.9536 0.0477
-3.250 -0.0337 0.01313 0.00482 -0.0544 0.9482 0.0501
-3.000 -0.0018 0.01275 0.00439 -0.0552 0.9425 0.0525
-2.750 0.0320 0.01242 0.00401 -0.0564 0.9375 0.0556
-2.500 0.0633 0.01198 0.00355 -0.0571 0.9293 0.0611
-2.250 0.0964 0.01168 0.00320 -0.0581 0.9212 0.0655
-2.000 0.1285 0.01132 0.00293 -0.0589 0.9124 0.0776
-1.750 0.1580 0.01104 0.00285 -0.0593 0.9034 0.1397
-1.500 0.1883 0.01089 0.00277 -0.0597 0.8962 0.1691
-1.250 0.2165 0.01074 0.00272 -0.0598 0.8860 0.2021
-1.000 0.2443 0.01061 0.00267 -0.0596 0.8739 0.2291
-0.500 0.2982 0.01033 0.00257 -0.0591 0.8485 0.2961
-0.250 0.3206 0.00946 0.00255 -0.0582 0.8352 0.5535
0.000 0.3815 0.00859 0.00267 -0.0648 0.8230 1.0000
0.250 0.4072 0.00863 0.00263 -0.0642 0.8058 1.0000
0.500 0.4330 0.00867 0.00260 -0.0636 0.7874 1.0000
0.750 0.4583 0.00874 0.00257 -0.0628 0.7632 1.0000
1.000 0.4829 0.00886 0.00253 -0.0618 0.7277 1.0000
1.250 0.5069 0.00904 0.00250 -0.0607 0.6792 1.0000
1.500 0.5286 0.00940 0.00247 -0.0592 0.5891 1.0000
1.750 0.5497 0.00992 0.00261 -0.0578 0.5324 1.0000
2.000 0.5737 0.01026 0.00280 -0.0570 0.5049 1.0000
2.250 0.5985 0.01053 0.00299 -0.0564 0.4843 1.0000
2.500 0.6226 0.01085 0.00319 -0.0558 0.4389 1.0000
2.750 0.6420 0.01165 0.00338 -0.0545 0.3100 1.0000
3.000 0.6623 0.01254 0.00378 -0.0534 0.2141 1.0000
3.250 0.6860 0.01301 0.00416 -0.0529 0.1873 1.0000
3.500 0.7103 0.01338 0.00449 -0.0524 0.1729 1.0000
3.750 0.7351 0.01370 0.00482 -0.0519 0.1621 1.0000
4.000 0.7593 0.01409 0.00517 -0.0514 0.1441 1.0000
4.250 0.7841 0.01440 0.00550 -0.0510 0.1272 1.0000
4.500 0.8082 0.01481 0.00582 -0.0505 0.0971 1.0000
4.750 0.8312 0.01538 0.00628 -0.0498 0.0776 1.0000
5.000 0.8519 0.01632 0.00697 -0.0488 0.0317 1.0000
5.250 0.8742 0.01704 0.00771 -0.0479 0.0247 1.0000
5.500 0.8962 0.01787 0.00875 -0.0468 0.0207 1.0000
5.750 0.9180 0.01866 0.00968 -0.0459 0.0171 1.0000
6.000 0.9384 0.01967 0.01084 -0.0448 0.0148 1.0000
6.250 0.9543 0.02132 0.01265 -0.0429 0.0131 1.0000
6.500 0.9746 0.02227 0.01374 -0.0417 0.0125 1.0000
6.750 0.9938 0.02346 0.01506 -0.0403 0.0119 1.0000
7.000 1.0130 0.02467 0.01642 -0.0390 0.0109 1.0000
7.250 1.0324 0.02582 0.01771 -0.0378 0.0095 1.0000
7.500 1.0509 0.02715 0.01920 -0.0365 0.0084 1.0000
7.750 1.0681 0.02882 0.02104 -0.0350 0.0079 1.0000
8.000 1.0845 0.03062 0.02310 -0.0335 0.0075 1.0000
8.250 1.0996 0.03258 0.02527 -0.0319 0.0072 1.0000
8.500 1.1127 0.03470 0.02764 -0.0301 0.0070 1.0000
8.750 1.1233 0.03704 0.03025 -0.0280 0.0068 1.0000
9.000 1.1308 0.03957 0.03307 -0.0258 0.0067 1.0000
9.250 1.1343 0.04232 0.03612 -0.0231 0.0065 1.0000
9.500 1.1338 0.04515 0.03926 -0.0202 0.0065 1.0000
9.750 1.1274 0.04790 0.04229 -0.0167 0.0064 1.0000
10.000 1.1173 0.05076 0.04540 -0.0132 0.0064 1.0000
10.250 1.1052 0.05396 0.04886 -0.0106 0.0064 1.0000
10.500 1.0913 0.05761 0.05276 -0.0090 0.0064 1.0000
10.750 1.0763 0.06179 0.05717 -0.0086 0.0065 1.0000
11.000 1.0597 0.06675 0.06236 -0.0096 0.0065 1.0000
11.250 1.0421 0.07262 0.06845 -0.0121 0.0065 1.0000
11.500 1.0237 0.07984 0.07588 -0.0165 0.0066 1.0000
11.750 1.0036 0.08875 0.08500 -0.0227 0.0067 1.0000
12.000 0.9802 0.10010 0.09654 -0.0305 0.0068 1.0000
12.250 0.9451 0.11731 0.11391 -0.0405 0.0072 1.0000
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Polar data table (+)
Polar graphs
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