D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: D.G.A. 1182 (dga1182-il) Reynolds number: 1,000,000 Max Cl/Cd: 57.61 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dga1182-il-1000000.txt Download as CSV file: xf-dga1182-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6886 0.08764 0.08416 0.0113 0.1499 0.0069
-8.250 -0.6964 0.08073 0.07728 0.0031 0.1498 0.0069
-8.000 -0.7000 0.07402 0.07049 -0.0028 0.1497 0.0069
-7.750 -0.6991 0.06894 0.06530 -0.0056 0.1498 0.0069
-7.500 -0.6946 0.06429 0.06054 -0.0073 0.1499 0.0070
-7.250 -0.6869 0.05991 0.05602 -0.0084 0.1501 0.0071
-7.000 -0.6764 0.05570 0.05167 -0.0090 0.1503 0.0073
-6.750 -0.6634 0.05162 0.04741 -0.0092 0.1505 0.0076
-6.500 -0.6479 0.04761 0.04321 -0.0091 0.1508 0.0079
-6.250 -0.6297 0.04356 0.03896 -0.0087 0.1511 0.0085
-6.000 -0.6038 0.04058 0.03575 -0.0076 0.1515 0.0093
-5.750 -0.5827 0.03757 0.03250 -0.0068 0.1520 0.0095
-5.500 -0.5626 0.03440 0.02904 -0.0059 0.1524 0.0095
-5.250 -0.5418 0.03136 0.02570 -0.0050 0.1529 0.0096
-5.000 -0.5201 0.02844 0.02244 -0.0041 0.1534 0.0096
-4.750 -0.5014 0.02240 0.01579 -0.0025 0.1536 0.0100
-4.500 -0.4780 0.02028 0.01354 -0.0023 0.1542 0.0110
-4.250 -0.4522 0.01977 0.01298 -0.0023 0.1532 0.0125
-3.500 -0.3716 0.01717 0.00992 -0.0012 0.1471 0.0147
-3.250 -0.3477 0.01381 0.00629 0.0004 0.1467 0.0110
-3.000 -0.3218 0.01298 0.00537 0.0008 0.1461 0.0112
-2.750 -0.2951 0.01253 0.00487 0.0011 0.1456 0.0122
-2.500 -0.2681 0.01221 0.00449 0.0012 0.1447 0.0135
-2.250 -0.2409 0.01196 0.00417 0.0013 0.1439 0.0144
-2.000 -0.2133 0.01187 0.00402 0.0013 0.1428 0.0152
-1.750 -0.1863 0.01146 0.00346 0.0015 0.1417 0.0179
-1.500 -0.1590 0.01147 0.00339 0.0015 0.1401 0.0211
-1.250 -0.1315 0.01154 0.00339 0.0015 0.1374 0.0241
-1.000 -0.1047 0.01085 0.00319 0.0015 0.1357 0.1828
-0.750 -0.0769 0.01080 0.00315 0.0015 0.1344 0.1989
-0.500 -0.0494 0.01074 0.00310 0.0014 0.1332 0.2133
-0.250 -0.0228 0.01044 0.00310 0.0014 0.1319 0.3365
0.000 0.0054 0.01065 0.00332 0.0013 0.1307 0.3520
0.250 0.0335 0.01090 0.00352 0.0012 0.1295 0.3580
0.500 0.0612 0.01121 0.00378 0.0011 0.1268 0.3611
0.750 0.0901 0.01089 0.00352 0.0010 0.1239 0.3634
1.000 0.1183 0.01091 0.00355 0.0009 0.1221 0.3652
1.250 0.1465 0.01093 0.00357 0.0008 0.1203 0.3668
1.500 0.1748 0.01091 0.00356 0.0007 0.1186 0.3682
1.750 0.2037 0.01075 0.00341 0.0006 0.1166 0.3696
2.000 0.2324 0.01069 0.00334 0.0005 0.1150 0.3711
2.250 0.2600 0.01079 0.00348 0.0004 0.1098 0.3722
2.500 0.2877 0.01088 0.00357 0.0004 0.0922 0.3729
2.750 0.3185 0.01024 0.00280 0.0002 0.0842 0.3734
3.000 0.3463 0.01026 0.00279 0.0001 0.0770 0.3742
3.250 0.3740 0.01032 0.00285 0.0001 0.0692 0.3753
3.500 0.4013 0.01047 0.00304 0.0000 0.0604 0.3762
3.750 0.4282 0.01077 0.00324 0.0000 0.0422 0.3770
4.000 0.4555 0.01099 0.00345 0.0000 0.0384 0.3778
4.250 0.4830 0.01119 0.00368 0.0000 0.0362 0.3785
4.500 0.5104 0.01140 0.00398 0.0000 0.0352 0.3792
4.750 0.5376 0.01166 0.00431 0.0000 0.0345 0.3799
5.000 0.5646 0.01200 0.00475 0.0001 0.0339 0.3809
5.250 0.5911 0.01242 0.00525 0.0002 0.0329 0.3819
5.500 0.6183 0.01255 0.00543 0.0002 0.0323 0.3828
5.750 0.6452 0.01277 0.00570 0.0002 0.0314 0.3837
6.000 0.6720 0.01299 0.00597 0.0002 0.0298 0.3844
6.250 0.6986 0.01326 0.00628 0.0002 0.0281 0.3850
6.500 0.7249 0.01356 0.00661 0.0003 0.0262 0.3855
6.750 0.7489 0.01458 0.00778 0.0006 0.0226 0.3860
7.000 0.7771 0.01431 0.00748 0.0004 0.0218 0.3864
7.250 0.8043 0.01430 0.00748 0.0003 0.0197 0.3869
7.500 0.8308 0.01451 0.00760 0.0002 0.0160 0.3873
7.750 0.8566 0.01487 0.00800 0.0003 0.0136 0.3891
8.000 0.8820 0.01540 0.00849 0.0005 0.0111 0.3908
8.250 0.9065 0.01625 0.00952 0.0008 0.0096 0.3920
8.500 0.9319 0.01677 0.01012 0.0010 0.0088 0.3927
8.750 0.9569 0.01739 0.01081 0.0011 0.0079 0.3935
9.000 0.9810 0.01826 0.01178 0.0014 0.0071 0.3943
9.250 1.0007 0.02031 0.01418 0.0022 0.0063 0.3950
9.500 1.0224 0.02177 0.01589 0.0028 0.0061 0.3957
9.750 1.0452 0.02293 0.01722 0.0031 0.0059 0.3966
10.000 1.0667 0.02442 0.01892 0.0036 0.0057 0.3974
10.250 1.0870 0.02618 0.02094 0.0041 0.0055 0.3982
10.500 1.1055 0.02826 0.02328 0.0047 0.0052 0.3990
10.750 1.1215 0.03077 0.02608 0.0055 0.0050 0.3997
11.000 1.1351 0.03383 0.02944 0.0063 0.0048 0.4003
11.250 1.1442 0.03744 0.03336 0.0072 0.0046 0.4009
11.500 1.1406 0.04317 0.03953 0.0084 0.0045 0.4017
|
Polar data table (+)
Polar graphs
<< Back to D.G.A. 1182 (dga1182-il)